ASME P T C * l l 84 W 0757670 0051269 9 W @ /

SPECIAL NOTICE

to

ANSI/ASME PTC 11-1984

FANS

ANSIlASME PTC 11-1984 was originally issued with an automatic addenda subscrip-
tion service. This service has been cancelled: This Code will be revised when the Society
approves the issuance of a new edition; therewill be no addenda or written interpretations
of the requirements of this Code issued to this edition.
Please see revised copyright page on the reverse.

C0052N

3ea2.l
COPYRIGHT American Society of Mechanical Engineers
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 Date of Issuance: October 30,1984

This Code will be revised when the Society approves the issuance of a new edition. There will be no
L addenda or written interpretationsof the requirementsof this Standard issuedto this edition.

This code or standard was developed under procedures accredited as meeting the criteria for Amer-
ican National Standards. The Consensus Committee that approved the code or standard was balanced
to assure that individuals from competent and concerned interests have had an opportunity t o partici-
pate. The proposed code or standard wasmade available for public review and comment which pro-
vides an opportunity for additional public input from industry, academia, regulatory agencies, and the
public-at-large.
ASME does not "approve,""rate," or "endorse"any item, construction, proprietary device,or
activity.
ASME does not take any position with respect to the validity of any patent rights asserted in con-
nection with any items mentioned in this document, and does not undertake to insure anyone utilizing
a standard against liability for infringement of any applicable Letters Patent, nor assume any such lia-
bility. Users of a code or standard are expressly advised that determination of the validity of any such
patent rights, and the risk of infringement of such rights, i s entirely their own responsibility.
Participation by federal agency representative(s) or person(s) affiliated with industry is not to be
interpreted as government or industry endorsement of this code or standard.
ASME does not accept any responsibility for interpretations of this document made by individual
volunteers.

No part of thisdocument may be reproduced in any form,

in an electronic retrieval system o~otherwise,
without the prior written permission of the publisher.

Copyright O 1984 by
THEAMERICAN SOCIETY OF MECHANICAL ENGINEERS
All Rights Reserved
Printed in U.S.A.

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 Fans

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 PERFORMANCE
TEST
Fans CODES

ANSI/ASME PTC 11-1984

T HAEM E R I C A N SOCIETY OF MECHANICA

E LN G I N E E R S

United Engineering Center 345 East Street

47th New York, N.Y. 10017

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 Date of Issuance: October 30, 1984

The 1984 Edition of this Code is beingissued with an automatic addenda subscription
service.Theuse of an addenda allows revisions made in response to public review com-
ments or committee actionsto be published every 2 years; revisions published in addenda
will becomeeffective 6 monthsaftertheDate of Issuance of theaddenda.Thenext
edition of thisCode is scheduled for publication in 1989.
ASME issues written replies to inquiries concerning interpretationsof technical aspects of
this Code. The interpretations will be included with the above addenda service. Interpre-
tations are not part of the addenda to the Code.

This code or standard was developed under proceduresaccredited as meeting the criteria for Amer-
ican National Standards, The Consensus Committee that approved the code or standard was balanced
to assure that individuals from competent and concerned interests have had an opportunity to partici-
pate. The proposed code or standard wasmade available for public review and comment which pro-
vides an opportunity for additional public input from industry, academia, regulatory agencies, and the
public-at-large.
ASME does not "approve,""rate," or "endorse" any item, construction, proprietary device,or
activity.
ASME does not take any position with respect to the validity of any patent rights asserted in con-
nection with any items mentioned in this document, and does not undertake to insure anyone utilizing
a standard against liability for infringement of any applicable Letters Patent, nor assume any such lia-
bility. Users of a code or standard are expressly advised that determination of the validity of any such
patent rights, and the risk of infringement of such rights, i s entirely their own responsibility.
Participation by federal agency representative(s) or person(s1 affiliated with industry is not to be
interpreted as government or industry endorsement of this code or standard.
ASME does not accept any responsibility for interpretations of this document made by individual
volunteers.

No part of thisdocument may be reproduced in any form,

in an electronic retrieval system or otherwise,
without the prior written permission of the publisher.

Copyright O 1984 by
THEAMERICAN SOCIETY OF MECHANICAL ENGINEERS
All Rights Reserved
Printed in U.S.A.

COPYRIGHT American Society of Mechanical Engineers

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 ASME P T C * l l &L( m 0759670 005327g 2 m

FOREWORD

(This Foreword is not part of ANSVASME PTC 11-1984.)

PTC 11-1946, entitled Test Code for Fans, was published by the Society in 1946. As
noted in its Foreword, the personnel of the committee that developed the Code
consisted of members of theAmerican Society of Heating and VentilatingEngineers,
the National Association of Fan Manufacturers, and the American Society of
Mechanical Engineers. The Code, as written, was basically a laboratory test standard in
that it provided instructionsfor arrangement oftest equipment such as ducts, plenum
chamber, and flow straighteners, as well as instruments. It even stated that the test
could beconducted in the manufacturer's shops, the customer's premises, or
elsewhere. This Code was widelydistributed and the principles set forth in it
undoubtedly provided the basis for many other laboratory standards for testing fanì.
Most ASME Power Test Codes (later called Performance Test Codes) provided
instructions for testing equipment after it was installed. Since PTC 11-1946 was basically
a laboratory standard, it was allowed to go out of print with the expectation that a
revised code would be written that would providedirections for site testing of fans.
In July of1961, a new PTC 11 Committee was formed. Several drafts were prepared,
but all of them essentially provided laboratory directions. This Committee still con-
sidered field or site testing to be impractical unless laboratory conditions could be
duplicated.
The PTC 11 Committee was reorganized in 1971. It initially attemptedto resolve the
difficulties ofsite testing by resorting to modeltesting. This was not acceptable to the
Society. Ultimately, procedures were developed that could used
bein the field without
the need to modify the installation so as to condition the flow measurement.
for The
Committee performed tests to determinethe acceptabilityof these procedures. These
tests included full-scalefield tests of twolarge mechanical-draft fans as well as various
laboratory tests of various probes for measuring flow angles and pressures. Subsequent
tests (Ref. 19) performed independently of the Committee have demonstrated the
practicability of this Code with regard to both manpower and equipment in a large-
power-plant situation.
The Committee has also monitored the progress of an International Committee
which was writing testcodes for fans. While this Committee, I S 0 117, had not
completed its work, it was obvious that several things they were doing should be
incorporated in PTC 11. The major item contributed by I S 0 117 is the concept of
specific energy(also called work per unit mass) which, when combined with mass flow
rate, provides an approach to fan performance thatcan be used instead of thevolume
flow rate/pressure approach. I S 0 also recognizes the distributionality of velocity
across the measuring plane and PTC 11 incorporates provisionsto account for this.
This Ccde was approved by the Board on PerformanceTest Codeson M a y 19,1983. It
was approved and adopted by the AmericanNational Standards Institute, Inc., on ..

March 23,1984.

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 ASME PTC*LL 8 4 m ' 0 7 5 7 6 7 0 0 0 5 3 2 7 5 4

PERSONNEL O F PERFORMANCE TEST CODE COMMITTEE NO. 11

ON FANS

[The following is the roster of the Committeeat the timeof approval of this Code.)

OFFICERS

R. Jorgensen, Chairman
C. O. Wood, Vice Chairman
M, M. Merker, Secretary

COMMITTEE PERSONNEL

H. R. Bohanon, ACME Engineering and Manufacturing Co.

W. R. Campbell, Foster Wheeler Boiler Corp.
M. J. Dorsey, TRW, Inc.
P. M. Cerhart, Department of Mechanical Engineering, University of Akron
R. E. Henry, Sargent & Lundy Engineers
R. Jorgensen, Buffalo Forge Co.
S. W.Lovejoy, Long Island Lighting Co.
F. S. Nolfe, Stearns-Roger, Inca*
S. P. Nuspl, Babcock & Wilcox
R. F. Storm, Flame Refractories, Inc.**
C. O. Wood, Fan Systems Co.***

Formerly with
*TLT-Babcock
**Carolina Power & Light
***Westinghouse Electric Corp.

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 BOARD ON PERFORMANCE TEST CODES

C. B. Scharp, Vice President

D. W. Anacki G. J. Gerber W. G. McLean

R. P. Benedict A. S. Grimes J. W. Murdock
K. C. Cotton K. G. Grothues L. C. Neale
W. A. Crandall R. Jorgensen R. J. Peyton
R. C. Dannettel W. C. Krutzsch W. A. Pollock
J. S. Davis A. Lechner W. O. Printup
J. H. Fernandes P. Leung J. C. Westcott
W. L. Carvin S. W. Lovejoy

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 ASME P T C m 1 1 8 4 m 0 7 5 7 b 7 00 0 5 1 2 7 7 8 m

CONTENTS

Foreword ........................................................ iii

S t a n d a r dCs o m m i t t e R
e oster ....................................... v

Section
1 INTRODUCTION ................................................... 1
1.1 General ...................................................... 1
1.2 Objectives ................................................... 1
1.3 Scope ....................................................... 1
1.4 Applicability ................................................. 1

2 DEFINITIONS AND DESCRIPTION OF TERMS ......................... 3

2.1 Symbols ..................................................... 3
2.2 Temperature ................................................. 7
2.3 Specific
Energyand
Pressure ................................... 7
2.4 Density ...................................................... 8
2.5 Fan Boundaries ............................................... 8
2.6 Fan Performance ............................................. 8
2.7 Fan Operating Conditions ........ .-........................... 12
2.8 Errors and
Uncertainties ....................................... 12

3 GUIDING PRINCIPLES .............................................. 13

3.1 Introduction ................................................. 13
3.2 Prior Agreements ............................................. 13
3.3 Code
Philosophy ............................................. 13
3.4 System
Design
Considerations ................................. 15
3.5 InternalInspectionandMeasurement of CrossSection ........... 15
3.6 Test
Personnel ............................................... 16
3.7 Point of Operation ........................................... 16
3.8 Method of Operation During
Test .............................. 16
3.9 Inspection.
Alterations.
Adjustments ........................... 16
3.10 Inconsistencies ............................................... 16
3.11 MultipleInlets or Ducts ....................................... 16
3.12 Preliminary
Test .............................................. 17
3.13 Reference Measurements ..................................... 17

4 INSTRUMENTS AND METHODS OF MEASUREMENT .................. 19

4.1 General
Considerations ....................................... 19
4.2 Traverse
Specifications ........................................ 19
4.3 AtmosphericPressure ......................................... 23
4.4 Temperature ................................................. 23
4.5 Moisture .................................................... 27
vii

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 Gas
4.6 Composition ............................................. 27
Pressure
4.7 Sensing .............................................. 27
Pressure
4.8 Indicating ........................................... 32
Yaw
4.9 ................................................
and Pitch 33
4.10 RotationalSpeed............................................. 33
4.11 .................................................
Input Power 35

5 CALCULATIONS .................................................... 37
5.1 General Considerations ....................................... 37
5.2 Correction.of Traverse Data ................................... 37
Gas
5.3 Composition ............................................. 39
5.4 Density ...................................................... 42
5.5 Fluid Velocity ................................................ 42
5.6 MassFlowRate ............................................... 44
5.7 Flow Weighted Averages ...................................... 44
5.8 Fan Input Power .............................................. 45
5.9 Fan Spee.d (Slip Method) ...................................... 46
5.10 Mass FlowRate - SpecificEnergy Approach .................... 46
5.11 Volume Flow Rate - Pressure Approach ....................... 47
5.12 .................................................
Uncertainties 50

6 REPORT OF RESULTS ............................................... 57

6.1 General Requirements ........................................ 57
6.2 TestReport .................................................. 57

Figures
2.1 Typical Inlet and Outlet Boundaries ............................ 9
2.2 Typical Input PowerBoundaries ................................ 10 .
4.1 Sampling Point Details
(Rectangular Duct) ...................... 21
4.2 Sampling Point Details (Circular Duct) .......................... 22
4.3(a) Probe Orientation - Centrifugal Fans .......................... 24
4.3(b) Probe Orientation - Axial Fans ................................ 25
4.4
Fan Room Pressure ........................................... 26
4.5 Fechheimer Probe ............................................ 28
4.6 Five-Hole Probe .............................................. 29
4.7 Stream NozzleJet ........................................
Free 31
4.8 Typical Calibration Curves for a Five-Hole Probe ................ 34
5.1 PsychrometricDensity Chart ................................... 43
5.2 Compressibility Coefficients
(Volume Flow - Pressure Approach) ......................... 48

Table
4.1 Summary of Instrumentation Requirements ..................... 36

Appendices
A
Typical
Results
Summary and
Data
Sheets ............................ 59
B ComputerCode and Input Form ............................... 65
Sample
C Computer Output ..................................... 109
D Derivations of Uncertainty Equations ........................... 121
E Assigning Values to Primary Uncertainties ....................... 129
F References ................................................... 133

viii
d)

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 ASME P T C * 1 1 8 4 m 0757b70 0051279 L

ANSVASME PTC 11 -1 984

FANS ANAMERICANNATIONALSTANDARD

AN AMERICAN NATIONAL STANDARD

ASME PERFORMANCE TEST CODES

Code on
FANS

SECTION 1 - INTRODUCTION
1.1 GENERAL measured performance to that which would
prevail
under specified operating conditions.
This Codeprovides standard procedures for
conducting and reporting tests on fans, including
those of the centrifugal, axial, and mixed flow
1.3 SCOPE
types. The principal quantities that can be deter-
mined are: The scopeof this Code is limited to the testing of
( a ) fan mass flow rate, or alternatively, fan vol- fans after they have been installedin thesystems for
ume flow rate; whichtheywereintended.However,the same
(6) fan specific energy, or alternatively, fan pres- directions can be followed ina laboratory test. (The
sure; and laboratory test performance may not be duplicated
(c) fan input power. by a test after installationbecause of system effects.)
Hereinafter these parameters shall be inclusively The term fan impliesthat the machine is used
covered by the term performance. Additional quan- primarily for moving air or gas rather than compres-
tities that can be determined are: sion. The distinction between fans, blowers, ex-
(cf) gas properties at the fan inlet; and hausters, and compressors in common practice is
(e) fan speed; rather vague; accordingly, machines that bear any
hereinafter inclusively covered by the term operat- of these names may be tested under the provisions
ing conditions. Various otherquantities can be of this Code. (It is conceivable that these machines
determined, including: can also be tested under the provisions of PTC 10,
( f ) fan output power; Compressors and Exhausters.)
(g) compressibility coefficient; and This Code does notinclude procedures for
(h) fan efficiency. determining fan acoustical characteristics.

1.4 APPLICABILITY
1.2 OBJECTIVES
A Code test requires a largeinvestment of
The objectives of this Code are: manpower and equipment. This Code and PTC 1,
( a ) to provide therules for testing fans to deter- General Instructions, should be studied thoroughly
mine performance under actual operating condi- when preparing procedures for testing a fan. The
tions; and provisions of this Codeare mandatory for a Code
(6) to provide additional rules forconverting test as are the provisions of Part III of PTC 1-1980.

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 ANSI/ASME PTC I I -I 984
FANS ANAMERICANNATIONALSTANDARD

SECTION 2 - DEFINITIONS AND

DESCRIPTION O F TERMS

2.1 SYMBOLS
Unit/Value

ption Symbol SI

Symbols and SubscriptedSymbols

Cross-sectional area of duct ft2 m2
Parameter in Eq. (5.11-20) dimensionless dimensionless
Parameter in Eq. (5.10-7) dimensionless dimensionless
Cross-sectional area of calibration jet or ft2 m*
wind tunnel
(See pp. 6 and 7)
Drag coefficient of probesection dimensionless dimensionless
?itch pressure coefficient dimensionless dimensionless
Specific heat at constant pressure BtuAbm "F J/kg * K
Specific heat at constant volume Btu/lbm "F J/kg * K
Duct diameter ft m
Probe diameter ft m
Electric potential (voltage) V V
Specific kinetic energy Ib/lbm
ft Ilkg
Number of points factor dimensionless dimensionless
Steady operation factor forX where dimensionless dimensionless
X=m,Q,y,p,p,orN
Frequency Hz Hz
Local acceleration due to gravity ft/sec2 m/s2
(See p. 7)
Enthalpy Btu/lbm Ilkg
Electric current (amperage) A A
(See p. 7)
Probe total pressure coefficient dimensionless dimensionless
Probe velocitypressure coefficient dimensionless dimensionless
Compressibility coefficient dimensionless dimensionless
(mass flow - specific energy approach)
Compressibility coefficient dimensionless dimensionless
(volume flow - pressure approach)

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 ANSI/ASME PTC 1 1 - 1 984
AN AMERICANNATIONALSTANDARD FANS

2.1 SYMBOLS (cont'd.)

Unit/Value

Symbol Description U.S. Customary SI

Symbols and Subscripted Symbols(cont'd.)

Ratio of specific heats (cP/cv) dimensionless dimensionless
Mach number dimensionless dimensionless
Molecular weight Ibm/lbm-mol kg/kg-mol
M a s s flow rate Ibm/sec kg/s
Fanmass flow rate Ibm/sec kg/s
Rotational speed r Pm rev/s
Specified rotational speed rPm rev/s
Counts or number dimensionless dimensionless
Number of poles dimensionless dimensionless
Fan input power hP kW
Fan output power hP kW
Barometric pressure in. Hg k Pa
Saturated vapor pressure in. Hg k Pa
Fan static pressure in. wg [Note (I)] kPa
Fan total pressure in. wg k Pa
Fan velocity pressure in. wg k Pa
Partial pressure of water vapor in. Hg k Pa
Static pressure in. wg kPa
Absolute static pressure in. wa [Note (2)] k Pa
Total pressure in. wg k Pa
Absolute total pressure in. wa k Pa
Velocity pressure in. wg k Pa
Differential pressure in. wg k Pa
Fan volume flow rate cf m m3/s

Probe Reynolds Number dimensionless dimensionless

Specific gas constant ftIb/lbm. O R J/kg * K

(See p. 7)
Aspect parameter dimensionless dimensionless
Frontal area of probeexposed to calibration ft2 m*
stream
Specific humidity Ibm vapor/lbm dry gas kg vapor/kg dry gas

Specific humidity at saturation Ibm vapor/lbm dry gas kg vapor/kg dry gas
Absolute static temperature O R K
Absolute total temperature O R K
Dry-bulb temperature "F "C

Static temperature O F "C

Total temperature O F OC

Wet-bulb temperature O F "C

4

- .
"
---"-a
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 ASME P T C * l l 8 4 W 0757b70 0 0 5 3 2 8 2 3 W

ANSI/ASME PTC 1 1 -1 984

FANS A N AMERICAN NATIONAL STANDARD

2.1 SYMBOLS (cont'd.)

Unit/Value

Symbol Description US. Customary SI

Symbols and Subscripted Symbols (cont'd.)

t sec S

UX Absolute
uncertainty in X same as X same as X
Relative uncertainty i n X per unit per unit
Velocity fPm m/s
Electrical power input to motor kW kW
Volume fraction ofgas constituent whose ft3/ft3 m3/m3
chemical symbol i s X
X Function used to determine K, dimensionless dimensionless

YF Fan specific energy ft

Ib/lbm Vkg
z Function used to determine K, dimensionless dimensionless

Greek Symbols

a Kinetic energy correction factor dimensionless dimensionless

ß Parameter usedto correct probe calibration dimensionless dimensionless
for blockage
Fan efficiency percent or per unit percent or per unit
Motor efficiency percent or per unit percent or per unit
Fan static efficiency percent or per unit percent or per unit
Fan total efficiency percent or per unit percent or per unit
Power factor dimensionless dimensionless
Sensitivity coefficient various various
Dynamic viscosity Ibm/ft sec Pa . S
Density Ibm/ft3 kg/m3
Fan gas density Ibm/ft3 kg/m3
Fan mean density Ibm/ft3 kg/m3

Summation of corrected values over ...

n observations

Torque lb * ft Nem
Pitch angle deg. deg.
Yaw angle deg. deg.

Subscripts

C Converted value ... ...

dS Dry gas * I . ...
f Liquid ...
fS Liquid tovapor ... ...
6 Vapor ...
5

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 ANSVASME PTC 11 -1984
AN AMERICANNATIONALSTANDARD FANS

2.1 SYMBOLS (cont'd.)

Unit/Value
~~

Symbol Description U.S. Customary SI

Subscripts (cont'd.)
i Indicated value at a point ... *..
i Corrected value at a point ... ...
ma Moist air

mg Moist gas ... ...

R measurement
Reference ... ...
ref Value for calibration
reference
probe *.. *..
t Turbine and drive train ... ...
X Total value at plane x for A, h, and QF or ...
average valueat plane x for cp, eK, M , ps,
pf,T , ,t V, ( X ) , a,and P
Y Total value at plane y for A, m, and QFor
average value a t plane y for cp, eK, M , p,,
pt, T , tS, V, ( X ) , (Y,
and P
O Plane O (ambient) ... ...
1 Plane 1 (fan inlet) I I I

2 . Planeoutlet)
2 (fan ... ...
3 Plane 3 (alternate velocity transverse ... ...
station)
Superscripts

R Random ... ...

S Systematic ... *..

Unit Conversions and Dimensional Constants

459.7" F 273.2"C
60 sedmin 1 .o s/s
1.o 1.8 O R/K
0.672 Ibm/ft sec 1.0 Pa S

1.0 Btu/lbm "F 4186 J/kg OC

2.96 X in. Hg/OF2 3.25 X kPa/"C
-1.59 X in. Hg/OF 18.6 X kPa/"C
0.41 in. Hg. 692 X kPa
2700O F 1500°C

70.77 Ib/ft2 in. Hg - IO3 J/m3 kPa

5.193 Ib/ft2. in. wg IO3 J/m3 kPa
1097 (Ibm/ft. min2-in. wg)1'2 &ÖÖÖ(m2/s2 kPa)1'2
13.62 in. wg/in. Hg 1.0 kPa/kPa
745.7 W/hp IO3 W/kW
5252 ftlbrev/hp.min (103/27r) N . m rev/kW * S

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 ANSVASME PTC 1 1 -1 984
FANS AN AMERICANNATIONALSTANDARD

2.1 SYMBOLS (cont'd.)

Unit/Value

Symbol Description U.S. Customary SI

Unit Conversion and Dimensional Constants (cont'd.)

s.. 550 ft * Ib/hp sec N m/kW - S

c17 *.. min ft3 in. wg/hp

6354 1.0 kJ/kW S

SC e . . Ibm/lb. 32.17 ft sec2 1.0 kg * m/N . s2

I ... 778.2.ft * Ib/Btu 1.O J/J

R, ... Ib/lbm-mol 1545 ft O R 8314 J/kg-mol K

NOTES:
(I) in. wg stands for inches water gage
(2) in. wa stands for inches water absolute

2.2 TEMPERATURE approximation tothe temperatureof adiabatic

saturation.
2.2.1 Absolutetemperature ( T ) is the valueof
temperature when the datum i s absolute zero. It i s
2.2.6 Wet-bulb depression i s thedifferencebe-
measured in kelvins or degrees Rankine. The abso-
tween the dry-bulb and wet-bulb temperatures at
lute temperaturein degrees Rankine is the temper-
the same location.
ature in degrees Fahrenheitplus 459.7 and the
absolute temperaturein kelvins is the temperature
in degrees Celsius plus 273.2. 2.3 SPECIFICENERGY A N D PRESSURE
2.2.2 Static temperature (tS, T,) is the temperature 2.3.1 Specific energy is energy per unit mass. Spe-
measured in such a way that no effectis produced cific kinetic energyis kinetic energy per unitmass
by the velocity of the flowing fluid. It would be and is equal to one-half the square of the fluid
shown by a measuring instrument moving a t the velocity. Specific potential energy is potential en-
same velocity as the moving fluid. Absolute static ergy per unit mass and i s equal to the gravitational
temperature is used as a property in defining the acceleration multiplied by the elevation above a
thermodynamic state of the fluid. specified datum. Fluid pressure divided by density
i s sometimes called specificpressure energy and is
2.2.3 Total temperature ( t t , Tt), sometimes called considered a type of specificenergy; however, this
stagnationtemperature, is the temperaturethat term is more properly called specific flow work,
would be measuredwhen a moving fluidis brought
to rest and its kinetic potential energies are con- 2.3.2 Pressure is normal force per unitarea. Since
verted to an enthalpy rise by an isoenergetic pressure divided by density may áppear in energy
compression from the flow condition to thestag- balance equations, it is sometimes convenient to
nation condition.At any point ina stationary body consider pressure as a typeofenergyper unit
of fluid, the static temperature and the total tem- volume.
perature are numerically equal.
2.3.3 Absolute pressure is the value of a pressure
2.2.4 Dry-bulb temperature ( t d ) is the temperature whenthedatum i s absolutezero. It is always
measured by a drythermometer orotherdry positive.
sensor.
2.3.4 Barometric pressure ( p b ) is the absolute pres-
2.2.5 Wet-bulb temperature ( t w ) is the temperature sure exerted by the atmosphere.
measured by a thermometer or other sensor cov-
ered bya water-moistened wickand exposed to gas 2.3.5 Differential pressure (Ap) is the difference
in motion. When properly measured, it is a close between any two pressures.
7

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 ~~ ASME PTC*:LL A4 M

ANSI/ASME PTC 11-1 984

AN AMERICANNATIONALSTANDARD FANS

2.3.6 Cage pressure is the value of a pressure when 2.4.2 Specifichumidity(S)is the mass of water vapor
the datum is the barometricpressure at the pointof per unit mass of dry gas.
measurement. It is thedifference between the
absolute pressure at a point and the pressure of the
ambient atmosphere in which the measuring gage
is located. It may be positive or negative.
2.5 FAN
BOUNDARIES
The fan boundaries are defined as the interface
2.3.7 Static pressure (ps,ps,) is the pressure mea- between the fan and the remainder of the system.
sured in such a manner that no effect is produced
These boundaries may differ slightly from fan to
by the velocity of the flowing fluid. Similar to the fan.Thefanaccepts power at its inputpower
static temperature, it would be sensed by a mea- boundary and moves a quantity of gas from its inlet
suring instrument moving at the same velocity as boundary to its outlet boundary and in theprocess
the fluid.Static pressure maybe expressed as either increases the specific energy and pressure of this
an absoluteor gage pressure. Absolute static pres- gas. The inlet boundary may be specified to include
sure is used as a property in defining the thermo- inlet boxes, silencers, rain hoods, or debris screens
dynamic state of the fluid. as a part of the fan, Thé outlet boundary may be
specified to includedampers or a diffuser as a part
2.3.8 Total pressure (pt,pta),sometimes called the of the fan. The inputpower boundary may be
stagnation pressure, would be measured when a specified to includethe fan-to-motor couplingor a
moving fluid is brought torest and its kinetic and speed reducer as part of the fan. See Figs. 2.1 and
potential energies areconverted to an enthalpy rise 2.2.
by an isentropic compression from the flow condi-
tion to the stagnation condition. It is the pressure
sensed by an impact tube orby the impact hole of a
Pitot-static tube when the tube is aligned with the 2.6 FAN
PERFORMANCE
local velocity vector. Totalpressure may be ex-
pressed as either an absoluteor gage pressure. In a 2.6.1 General. Fan performance can be expressed
stationary body of fluid, the static and total pres- in terms of different sets of parameters. This Code
sures are numerically equal. provides the user with two choices. One set uses
mass flow rate and specific energy. The other uses
volume flowrate and pressure. The product ofmass
2.3.9 Velocity pressure (pv),sometimes called dy- flow rate and specific energy and the product of
namic pressure, is defined as the product of fluid volume flow rate, pressure, and a compressibility
density and specifickineticenergy. Hence,velocity coefficient are each designated fan output power.
pressure is kinetic energy per unit volume. If However,values of output powercalculated by the
compressibility can be neglected, it is equal to the two methods are slightly different [Appendix F, Ref.
difference of thetotal pressure and the static (1)l.
pressure at the same point in a fluid and is the
differential pressure which would be sensed by a
2.6.2 The M a s s FlowRate - SpecificEnergy
properly aligned Pitot-static tube. In this Code the
Approach. The fan performance parameters that
indicated velocity pressure (pvi)shall be corrected
are associated with this approach are defined as
for probe calibration, probe blockage, and com-
follows.
pressibility before it can be called velocity pressure.
(a) Fan mass flow rate (hF) is the mass of fluid
passing through thefan per unit time.
(b) Fan specific energy (yF)is the work per unit
mass which would be done on the gas in an ideal
2.4 DENSITY
(frictionless) transition betweenthe actual inlet and
2.4.1 The density ( P ) of a fluid .is its mass per unit outlet states. Theideal work done on a unit mass of
volume. The density can be given static and total fluid is equal to the integral of the differential of the
values in afashion similar to pressure and tempera- static pressure divided by the fluid density for the
ture. If the gas is at rest, staticand total densities are fan flow process plus changes of specific kinetic
equal. energy and specific potential energy across the fan.

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ANSI/ASME PTC 11 -1 984

FANS A N AMERICAN NATIONAL STANDARD

Centrifugal Fans

I Silencer I I
o o o 4
o
Inlet box Inlet box

Fan Diffuser

L
Axial Fans
Q
GENERAL NOTES:
The inlet boundary is a t @ 0
for a centrifugal or axial fan .furnished with an inlet box or a t
@ @ if a silencer is considered a part of the fan.
The outlet boundary is a t @@ for a centrifugal fan without a diffuser or a t @@ if a
diffuser is part of the fan.

A n axial fan is usually furnished with a diffuser.

FIG. 2.1 TYPICAL INLET A N D OUTLET BOUNDARIES

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The fan specific energy is the average of the ideal 2.6.3 TheVolume Flow Rate - Pressure Ap-
work forall fluid particles passing through thefan. proach. The fan performance parameters associ-
Refer to Par. 5.7 for appropriate averages. ated with this approach are defined as follows.
Only the component of velocity in thenominal (a) Fan volume flowrate (QF) is the fan mass flow
direction of flow shall be taken into account when rate divided by the fan gas density.
determining the specific kinetic energy. It is cus- ( 6 ) Fan pressure. In this approach, three fan
tomary to assume that changes in potential energy pressures aredefined:
are negligible in fans. (7) Fan total pressure (P,() is the difference
between the average total pressure at the fan outlet
and the average total pressure at the fan inlet. Only
(Y, = l25+
1 P
eK2 - e,l) the component velocity of in thenominal direction
of flowshall be taken into account whendetermin-
ing fan total pressure. Referto Par. 5.7for appropri-
For anincompressible flow process, the product ate averages. It is customary t o assume that pressure
of fan specific energy and fluid density is equal to changes due to elevation changes arenegligible in
the fan total pressure. For a nonconstant density fans.
process, fan specific energy can be approximated (2) Fan velocitypressure ( p F v i)s the productof
by assuming somethermodynamic process within the average density and average specific kinetic
the fan in order to perform the pressure-density energy a t the fan outlet. Refer to Par. 5.7 for the
integfation. appropriate averages.
(c) Kinetic energy correction factor (a)is a di- (3) Fan static pressure (P,) is the difference
mensionless factor used to account for the dif- between the fan total pressure and the fan velocity
ference betweenthe trueaverage kinetic energy of pressure. Therefore, fan static pressure is the dif-
the fluid and the kineticenergy calculated as one- ference between the average static pressureat the
half the square of theaverage velocity. fan outlet and the average total pressure at the fan
(d) Fan meandensity (P,,,) is the ratio of the inlet. Refer to Par. 5.7 for appropriate averages.
pressure change across the fan to the thermo- (c) Fan gas density (,OF) is the totaldensity of the
dynamicpathintegralof the differential of the gas at fan inlet conditions.
pressure divided by thedensity. ( d ) Fan output power(Po) equals the product of
fan volume flow rate, fan total pressure, and com-
pressibility coefficient K,.
(Pm = ( P 2 - Pd//
1
-)
dP

P
(e)The compressibility coefficient (K,) is a di-
mensionless coefficient employed to account for
compressibility effects [Ref. (4)1 and is calculated
In this approach, mean density is approximated according to the procedure given in Par. 5.11.4 [Ref.
by thearithmetic mean of inletand outlet densities. (1911.
( f ) Fan efficiency. I n this approach,fan ef-
(Pm = (P1 + P 2 1 4 ficiency is expressed as either fan total efficiency or
fan static efficiency.
(e) Fan output power(Po) i s equal to the product (7) Fan total efficiency ('v1) is the ratio of fan
output power to fan input power. This may alsobe
of fan mass flow rate and fan specific energy. Since
called total-to-total efficiency.
mass flow rate equals the product of volume flow
rate and density at a particular plane, fan output (2) Fan static efficiency (vs) is the ratio of fan
power can also be expressed as the product of fan output power to fan input power, in which thefan
inlet density, fan inlet volume flow rate, and fan outputpower is modified by deletingthe fan
specific energy. velocity pressure. This mayalso be called total-to-
static efficiency.
( 0 The compressibility coefficient (/$,), defined
as the ratio of the fan inlet density to thefan mean
density, is useful in this approach.
(8)Fan efficiency (v)is the ratio of thefan output 2.6.4 Fan input power (P,) i s the power required
power to the fan input power. In this approach to drive the fan and any elements in the drive
there is only one definition fan of output powerso train that are considered to be within the fan
there is only one definition of fan efficiency. boundaries.
II

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ANSI/ASME PTC 1 1 - 1 984

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2.7 FANOPERATING CONDITIONS that prevent a measurement system from delivering

the same reading when supplied with the same
Fan operating conditions are specified by the
input. Random uncertainties can bereduced by
speed of rotation of the fan, and sufficient infor-
replication and averaging [Ref. (3)].
mation to determine the average gas properties
including pressure, temperature, density, viscosity,
gas constants, and specific heats at the fan inlet, 2.8.4 Systematic uncertainty (Us, us) is uncertainty
due to such things as instrument and operator bias
and changes in ambient conditions for the instru-
2.8 ERRORS A N D UNCERTAINTIES ments. Systematic uncertainty cannot be reduced
by increasing the number of measurements if the
2.8.1 Error is the difference betweenthe truevalue
equipment and the conditions of measurements
of a quantity and the measuredvalue.The true
remain unchanged [Ref. (3)].
value of an error cannot be determined.

2.8.2 Uncertainty is a possible value for the error

2.8.5 Confidence level (ec) is a percentage value
such that, if a very large number of determinations
[Ref. (2)]. It is also the interval within
which the true
value can be expected to lie with a stated proba-
of a variableare made, there is an e, percent
probability that the true value will fall within the
bility [Ref. (3)1. The uncertainty is used to estimate
interval defined by the meanplus or minus the
the error. Absolute uncertainty ( U ) has the same
uncertainty. A value for uncertainty is meaningful
units as the variable in question. Relative uncer-
only if it is associated with a specific confidence
tainty (u), also called per unituncertainty, is abso-
level. As used in this Code, all uncertainties are
lute uncertainty divided by the magnitude of the
assumed to be at the 95% confidence level. If the
variable and is dimensionless.
number of determinations of avariable is large and
ifthe valuesare normally distributed, theun-
2.0.3 Random uncertainty (UR,u R )is uncertainty certainty a t the 95% confidence level is approxi-
due to numerous small independent influences mately twice the standard deviation of the values.

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SECTION 3 - GUIDING PRINCIPLES

3.1 INTRODUCTION 3.3 CODE
PHILOSOPHY
In applying this Code to aspecific fan test, various 3.3.1 This Code offers the user the choice of ex-
decisions must be made. ThisSection explains what pressing fan performance in terms of mass flow rate
decisions shall be made and gives general guide- and specific energy or volume flowrate and pres-
lines for performinga Code test. sure. After reviewing bothmethods, the parties to
Any test shall be performed onlyafterthe fan has the test shall decide which method they intend to
been found by inspection to be in a satisfactory use. Once a method is selected then theprinciples
conditionto undergo the test. The owner and andprocedures foronly that method shall be
vendor shall mutually decide whenthe test is to be adhered to throughoutthe test, rather thancomming-
performed. ling the various aspects of the two methods [Ref.
The parties to the test shall be entitled to have (1)l.
present such representatives as are required for
them to be assured that the test is conducted in
accordance with this Code and with any written
3.3.2 The methods of this Code are based on the
agreements made prior to thetest.
assumption that fan pressures or specific energies
are measured sufficiently close to the fan bound-
aries that corrections for losses between the mea-
surement planes and the fan boundaries are not
required. It is not feasible to include methods
3.2 PRIOR
AGREEMENTS
for such corrections in this Code; therefore, if
Prior to conducting a Code test, written agree- such corrections are necessary,thetest cannot be a
ment shall be reachedby the parties to thetest on Code test.
the following items: For the purpose of determining proper average
( a ) object of test values of pressure, temperature, and density, it is
(6) duration of operationunder test conditions always necessaryto measure point velocities a t the
(c) test personnel and assignments fan boundaries. However, only the point velocities
(d) person in charge of test measured a t traverse planes conforming to the
(e) test methods to be used requirements ofthis Code (see Par. 4.2.3) shall be
( f ) test instrumentation and methods of cali- used for fan flow rate. If theconditions a t the fan
bration boundaries do not meet the criteria given in this
(g) locations for takingmeasurements andorien- Code for a suitable flow traverse, then point veloc-
tation of traverse ports ity measurements madea t the fan boundaries shal[
(h) number and frequency of observations be used only for determining averagevalues of
( i ) method of computing results pressure, temperature, density, andspecific kinetic
( j ) values of primary uncertainties energy and not for fan flow rate. If this condition
( k ) arbitrator to be used if one becomes desirable exists, then the
fan flow rate may be determinedat a
(I) applicable contract performancecurves and/ plane other than the fan boundary provided that no
or the specifiedperformanceandoperating fluid enters or leaves the duct between the fan
conditions boundary and the measurement plane. Although
( m ) fan boundaries the pointvelocities measured at the fan boundaries
(n) number of test runs may not conform to the requirements for a valid

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ANSI/ASME PTC 1 1-1 984

AN AMERICAN NATIONAL STANDARD FANS

flow traverse, they can provide a useful statistical simple arithmetic summing of the contribution of
basis for substantiating the fan flow rate. eachelemental area to the total flow.
Investigations
of flow measurement under conditions similar to
those expected in application of this Code have
3.3.3 For large ducts handling gas flows, often the demonstrated the validity of this approach [Refs.
only practicable method of gas flow measurement (71, (a), ( 9 ~ .
i s the velocity traverse method. This method shall
be considered the primary method for measuring
3.3.4 Due to the highly disturbed flow at the fan
flows of the type addressed by this Code. Other
boundaries and the errors obtained when making
methods of determining flow, including but not
measurements with probes unable to distinguish
limited to, stoichiometric methods (where appli-
directionality, probes capable of indicating gas
cable), ultrasonic methods, and methods using
direction and speed, hereinafterreferred to as
such devicesas flow nozzles, may be permitted if it
directional probes,are generally required. Only
can be shown that the accuracy of the proposed
the component of velocity normal to the elemental
method is at least equal to that of theprimary
area is pertinent to the calculation of flow. Mea-
method.
surement of this component cannot be accom-
In the velocity traversemethod, theduct is
plished by simply aligning a nondirectional probe
subdivided into a number of elemental areas and,
parallel to the duct axis, since such probes only
using a suitable probe, the velocity is measured a t a
indicate the correct velocity pressure when aligned
point ineach elemental area. The total flowis then
with thevelocity vector. Errors aregenerally due to
obtained by summing the contributions of each
undeterminable effects on the static (and to a lesser
elemental area. Within theframework of theveloc-
degree, total) pressuresensingholes.Therefore,
ity traverse method, many different techniques
adequate flow measurements in a highly disturbed
have been proposed for selecting the number of
region can only be made by measuring speed and
points at which velocity i s measured, for establish-
direction at each point and then calculating the
ing the elemental areas, and for summing (theoreti-
component of velocity parallel to the duct axis.
cally integrating) the contributions of each ele-
Onlyin somecircumstances(seePar. 4.7) may
mental area. Options that have beenproposed
nondirectional probes be used.
include the placing of points based on an assumed
(usually log-linear) velocity distribution [Refs. (4),
(5)], the use of graphical or numerical techniques to 3.3.5 Various methods of averaging arerequired to
integrate the velocity distribution over the duct calculate the appropriate values of the parameters
cross section [Refs. (5), ( 6 ) ] ,the use of equal ele- that determine fan performance. These methods,
mental areas with simple arithmeticsumming of the along with thelarge number of traverse points,the
contribution of each area to the total flow [Refs. directional probe, and requirements for measure-
(5), (7), ( 8 ) ] ,and the use of boundary layer correc- ments a t the fan boundaries make it possible to
tions to account for the thinlayer of slow-moving conduct an accuratefield test for most fan installa-
fluid near a wall. As a general rule, accuracyof flow tions [Refs. (8), (9), (IO)].
measurement canbe increased by eitherincreasing
the number of points in the traverse plane or by
3.3.6 The instruments and methods of measure-
using more sophisticated mathematical techniques
ment specified in this Code areselected on the
(e.g., interpolation polynomials, boundary layer
premise that only mild compressibility effects are
corrections) [Refs. (5), (7)]. It is more in line with the
present in the flow. Thevelocity,pressure, and
requirements of field testing as well as more realis-
temperature determinations provided for in this
tic in light of the varied distributions ofvelocity that
Code are limited to situations in which the gas is
may actually occur in the field, to obtain the desired
moving with a Mach number less than 0.4. This
accuracy of flow measurement by specifying mea-
corresponds to a value of (Ki pvi/psaj)of approxi-
surements at a relatively large number of points
mately 0.1 (see Par. 5.2.1).
rather than by relying on assumed velocity distribu-
tions or unsubstantiatedassumptions regarding
suchthings as boundary layereffects.Forthese 3.3.7 Although this Code provides methods for
reasons, this Code has elected to specify measure- conversion of measured fanperformance variables
ments at the centroids of equal elemental areas and to specified operating conditions, such conversions

14

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FANS AN AMERICAN NATIONAL STANDARD

shall not be permitted if the test speed differs by 3.4.1 Generally the most difficult parameter to
more than 10% from the specified speed or if the determine duringa field test i s the fan flow rate. If
test values of the fan inlet density ( p l ) or fan gas the following considerations can be made during
density ( p ~differ
) by more than 20% from specified the design of the fan andduct system, fan flow rates
values. will be easier to determine.
(a) Design of inlet and outlet ducts should avoid
internal stiffeners for three equivalent diameters
3.3.8 A question that invariably arises in connec-
both upstream and downstream ofthe fan bound-
tion withany test is "how accurate are the results?"
aries.
[Ref. (2)J.This question is addressed in this Codeby
(b) Abrupt changes in direction should not be
the inclusionof a completeprocedure for the
located at the fan boundaries.
evaluation of uncertainties, It is believed that all
(c) All transitions in duct size should be smooth.
significant sources of error in a fan test have been
( d ) A duct length of approximately 3 f t (1 m)
identified and addressedin this procedure.Since in
should be alloweda t the fan boundaries for insert-
fact any results basedon measurements areof little
ing probes. This section should be free of internal
value without an accompanying statement of their
obstructionswhich would affect the flow mea-
expected accuracy, uncertainty evaluationis made
surement and external obstructions which would
a mandatory part ofthis Code. impede probe maneuverability such as structural
steel, walkways, handrails, etc.
3.3.9 Commercially quotedfan performance is usu-
ally based on measurements made under labora- 3.4.2 Considerations thatcan be observed that will
tory conditions, In a laboratory test, a fan is oper-
aid the determination of fan input power are:
ated in a system specifically designed to facilitate ( a ) installing a calibrated drive train; or
accurate measurement of fan performance param- (b) allowing sufficient shaft length at the fan for
eters and to minimize those system effects that can the installation of a torque meter.
degrade fan performance [Refs. (4), (17)]. Compara-
tive fan tests conducted according to a laboratory
standard [Ref. (4)1and according to procedures of
3.5 INTERNALINSPECTIONAND
this Code have demonstrated that similar perfor- MEASUREMENT OF CROSS SECTION
mance ratings can be obtained if the fan is operated
under laboratory conditions [Ref. (18)]. An internal inspectionof the ductwork at planes
Theuser ofthisCodeshould be aware that where velocity and/or pressure measurements are
application ofthe procedures contained herein will to bemade shall be conductedby the parties to the
reveal the performanceof the test fan as it is test to insure that no obstructions will affect the
affected by the system in which it is installed. These measurements. Areas where there is an accumula-
in-situ performanceratings and ratings of thesame tion of dust such that the duct area i s significantly
fan based on laboratory tests or ratings of a model reduced shall be avoided as this indicates thatthe
fan based on laboratory tests may not be the same velocities are inadequate to prevent entraineddust
due to various effects generally called system ef- from settling. This dust settlement will in effect
fects [Ref. (17)l.Any methods for reconciliation of cause theduct cross-sectional area to decrease
in-situ performance ratings and laboratory based during the test. Where this situation exists, it i s
ratings are beyond the scope of this Code. recommended that velocity measurements b e
made in vertical runs.
The internal cross-sectional area shall be based
on theaverage of a t least four equally spaced mea-
surements across each duct dimension for nom-
3.4 SYSTEM DESIGNCONSIDERATIONS
inally rectangular ducts, and on the basis of the
There are field situations whereit is not possible average of at least four equally spaced diametral
to obtain sufficiently accurate measurements to measurements for nominally circular ducts. Suffi-
conform with this Code. Consideration of a few cient equallyspaced measurementsshall be used to
simple concepts when a new system is designed will limit theuncertainty in thearea to 0.3%. If the duct
facilitate fan testing as well as improve the fan sys- area is measured under conditions different from
tem performance. operating conditions, suitable expansion or con-

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ANSI/ASME PTC 11 -1 984

AN AMERICANNATIONALSTANDARD FANS

traction corrections for temperature and pressure off during the test. If soot blowing is necessary, it
shall be made. should be used throughout thetest. Theoperation
of pulverizers,stokers, baghouses,scrubbers,air
heaters,etc., shall not beallowed to affect the
3.6 TEST PERSONNEL results of the test.
3.6.1 A test team shall be selected that includes a
sufficient number of test personnel to record the 3.8.3 Adequate records of the positionof variable
various readingsin theallotted time.Test personnel vanes, variable blades, dampers, or other control
shall have the experience and training necessary to devices shall be maintained.
obtain accurate and reliable records. All data sheets
shall be signed by the observers. The use of au-
tomaticdata recording systemscanreduce the num- 3.9 INSPECTION, ALTERATIONS,
ber of people required. ADJUSTMENTS
Prior to the test, the manufacturer or supplier
3.6.2 The person in charge of the test shall direct shall have reasonable opportunity to inspect the
the test and shall exercise authority over all ob- fan and appurtenances for correction of noted de-
servers. This person shall certify that the test is fects, for normaladjustments to meet specifications
conducted in accordance with this Code and with and contract agreements, and to otherwise place
all written agreements made prior to thetest. This the equipmentin condition to undergo further op-
person may be required to bea registered profes- eration and testing. The partiesto thetest shallnot
sional engineer. alter or change the equipment or appurtenances in'
such a manner as to modify or void specifications or
contract agreements or prevent continuous and
3.7 POINT OF OPERATION reliable operation of the equipment at all capacities
and outputs under all specified operating condi-
This Code describes a method for determining tions. Adjustments to the fan that may affect test
the performance of a fan at a single pointof results are not permittedonce the test has started.
operation. If more than one point of operation is Should suchadjustments bedeemed necessary,
required, a test shallbe made for each. The parties prior test runsshall bevoided and the test restarted.
to the testmustagree prior to the tests on the Any readjustments and reruns shall be agreed to by
method ofvarying the system resistance to obtain the parties to the test.
the various points of operation. If performance
curves are desired,then theparties to thetest shall
agree beforehand as to thenumber and location of 3.10 INCONSISTENCIES
points required to construct the curves.
If inconsistencies in the measurements are ob-
served during the conduct of test, the the person in
3.8 METHOD O F OPERATION DURING TEST charge of the test shall
be permitted take
to steps to
remedy theinconsistency and to continue the test.
3.8.1 When a systemcontains fans operating in Any actions in this regard must be noted and are
tested shall be operatedin the
parallel, the fan to be subject to approval by the parties to thetest. Any
manual mode during the test and the remaining such action shall be fully documented in the test
fans in the system used to follow load variations. report.
The fanto be tested shall be operated at a constant
speed with constant damper and vane positions.
Various positions may be required for part-load 3.11 MULTIPLE INLETS O R DUCTS
tests.
If thereis more than onefan inlet, measurements
shall be obtainedat each inlet or eachin inlet duct.
3.8.2 The system shall be operated to maintain It is not permissible to measure the conditions a t
constant gas flows and other operating conditions. one inlet and assume the conditionsare the same
For example,for draft fans the boiler load shouldbe for all the inlets. Similarly, if the discharge duct
steady. Soot blowers should not becycled on and from a fan splits into two or more ducts and it is

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more practical to measure the conditions down- ( f ) fan outlet temperature (T2R)
stream of the split, then the conditions in each (g) total pressure rise across the fan (ptR)
branch ofthe duct shall be measured to determine ( h ) velocity pressure in eitherinletoroutlet
the total flow. plane
The measurement of speed and power made in
accordance with therequirements of Section 4 for
determining fan performance shall be used for
3.12 PRELIMINARY TEST
reference purposes. The reference measurements
Prior to performinga Code test, a preliminary test for pressure and temperature shall be in accor-
shall be made. The purpose of the preliminary test dance with Section 4 except a single point measure-
i s to train the observers, to determine if all instru- ment shall be used for each parameter instead of
ments are functioning properly, and to verify that the sampling grid. For purposes of referencemea-
the system and fan are in proper order to permit a surements, probes capable of sensing total pres-
valid Code test. The preliminary test can be con- sure, static pressure, velocity pressure, andternper-
sidered a Code test if agreed to by the parties to the ature connected to appropriate indicators shall be
test and all requirements of this Code are met. permanently fixed at central locations in the inlet
and outlet planes. These need not be directional
probes nor do they have to be calibrated since
measurements taken from these probes are for
3.13 REFERENCE MEASUREMENTS
reference purposes only. At 15 min intervals, the
For the purposes of determining that the system reference measurements of temperatureand pres-
has reached steady state, verifying the constancy of sure shall be averaged over a 2 min window of time
operatingconditions, and verifying that the fan and recorded, preferably on a graph. This may be
performs at a constant point of operation during done manually or automatically.
the test, the following reference measurements If the reference measurements indicate a de-
shall be made. parture from steady conditions at a fixed point of
( a ) speed (NR) operation which will cause an uncertainty uFSxin
(b) driver power, or some quantity proportional excess of I%, then the test shall be invalidated.
to driver power (e.g., IR, T,, W,, etc,) The person in charge of the test shall be solely
(c) fan inlet static pressure (plsR) responsible for deciding when operating condi-
(d) fan outlet static pressure tions are sufficiently constant to begin the test and
(e) fan inlet temperature (TIR) continue the test.

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ANSVASME PTC 1 1 -1 984

FANS AN AMERICAN NATIONAL STANDARD

SECTION 4 - INSTRUMENTS AND METHODS

O F MEASUREMENT

4.1 GENERAL CONSIDERATIONS is indicated. Any other extrapolation requires

agree-
ment among the parties.
4.1.1 Accuracy. The specifications for the selection
and calibration of instrumentsthat follow include
accuracy requirements. Unless otherwise stated, 4.1.3 MonitoringOperational Steadiness. It i s a
the specified accuracies are expressedin terms of requirement ofthis Code (see Par.3.13) that operat-
the maximum uncertaintyin any reading due to the ingconditions and pointofoperationbeheld
instrument based on a minimum confidence level steady during thetest. Readingsfor some of the test
of 95%. parameters,such as rotational speed and input
It is a requirement ofthis Codethat the parties to power, can be monitored for operational steadi-
the test agree in advance on the limits of possible ness. Other test variables,such as velocityand
measurement errors and test uncertainties. The pressure, are not uniformlydistributed; therefore,
parties should base theirjudgmentsofpossible test readings should not beused to monitoropera-
error on the references cited for each instrument, tional steadiness. Separateinstruments shall, there-
any records pertaining to the instrument to be fore, beused if thesevariables areto be monitored.
used, and their collective experience with similar Such monitoring instruments shall beheldin a
measurements. fixed positionrather than used to traverse the
plane.
Monitoring instruments shall be sensitive to
changes inthemonitored variables that would
4.1.2 Instrument Calibration. All instruments used affect results. However, the accuracy and calibra-
in a Code test shall be calibrated. It is not necessary tion requirements for the measuring instruments
to calibrate all instruments specificallyfor thetest if that follow can be relaxed or eliminated for instru-
the parties to the testagree onthevalidityof ments used only for monitoring purposes. It may
previous calibrations. even be desirable to use instruments with appreci-
The calibration data for an instrument shall be ably more dampingthan would be acceptablefor
represented as a continuous function which may be measuring instruments as long as the response is
determined by graphically fairing a smooth curve fast enough to adequately indicate departures from
among the calibration points, or by fitting, using operational steadiness.
the least squares methods, a mathematical curve
which has a number of fitting parameters less than
or equal to one-half of the number of calibration
4.2 TRAVERSE SPECIFICATIONS
points. In a polynomial, the fitting parameters are
the undeterminedcoefficients. In a power law 4.2.1 QuantitiesMeasured by Traverse. Because
formula, e.g.,axb,a andb are the fittingparameters. the distributions ofvelocity, pressure, temperature,
The fitting parameters forother casesmay be gas composition, and moisture across the ductcross
determined in a similar manner. section are nonuniform, each quantity shall be
Where the physical facts dictate, the calibration measured at a sufficientnumberofpoints to
function may be extrapolated to the origin. Calibra- facilitate the calibration aofproper average value.
tion data should cover the entire range of instru- Point values of all of these quantities are theoret-
ment readings, except where extrapolationto zero ically required a t every traverse plane, but this

19

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AN AMERICAN NATIONAL STANDARD FANS

Code recognizes that the distributions of gas com-

position and moisture aregenerally muchmore
uniform than the distributions of velocity, pressure,
4.2.3 Qualified Velocity Traverse Planes. To qualify
for a velocity traverse for purposes of determining
fan flow rate (see Par.3.3.2), a plane shall meet the
P
and temperature. Accordingly, the Code does not following specifications.
require that gas composition and moisture be (a) There shall be no internal stiffeners or other
measured at every point in a traverse plane. Simi- internal obstructions.
larly, the Code does not require that these quan- (b) There shall be no accumulation of dust or
tities be measured at all traverse planesif there are debris.
sound reasons to believe that there will be no ( c ) Thetraverse plane shall be atleast one
change between planes. There may also be cases damper blade width upstream o r ten damper blade
wherethe distribution oftemperature is quite widths downstream of a damper.
uniform. The parties may, therefore, agree to relax ( d ) A preliminary velocity traverse shall show
the requirement for temperature measurements if that the flowis reversed or essentially stagnantat no
they are convinced this will have a negligible effect more than 20% (preferably 0%) of the elemental
on the results. areas.
(e) There shall be no sudden change in either
cross-sectional area or duct direction.
4.2.2 Number of Traverse Planes. Two traverse
planes are required to determine specific output
(fan pressure or fan specific energy), except for the
case listed below. The preferred locations for the 4.2.4 Determinationof Sampling Grid. Measure-
traverseplanesare at the fan inlet and outlet ments shall be taken at centroids of equal ele-
boundaries, However, a slight offset, upstream or mental areas. However, allowing for probe stem
downstream, is usually required so that heavy droop and the need to avoid outsideduct bracing,
flanges or stiffeners do not have to be penetrated. the probe tip shall be locatedwithin a central area
Similarly, when dampersare located a t the fan the sides of which are no more than 30% of the
boundaries, it is more desirable to traverse slightly corresponding dimensions of the elemental area.
upstream of these dampers than downstream of Similarly, the probe tip may be outside the traverse
them. plane byno more than 30% of the largest elemental
Only one traverse plane is required to determine area dimension, and then onlyif the duct area is the
flow rate, but if both the inletplane and the outlet same as at the traverse plane. Refer to Figs. 4.1 and
plane qualify, each should be used. If neither the 4.2.
inlet plane nor the outlet plane qualifies, a third The number of test points shall be thelarger of
plane will be required for the velocity traverse to the following:
determine flow rate. ( a ) 24 points, or
I f at its inlet boundary thefan draws gas from an (b) not less than one point forevery 2 ft2 (0.2 m2)
essentially quiescent region of large volume and For measurement planes of rectangularand
the inletflow path is free fromobstructions (e.g., a square cross section, the aspect parameter S shall
fan drawing air fromthe atmosphere or a fan be between 2/3 and 4/3 where
located inside a large room), it is not necessary to
traverse the inlet todetermine specific output. The aspect ratio of elemental area
S=
inlet total pressure, inlet static pressure, and in- aspect ratio of duct cross section
let velocity pressureare all zero if the inlet re-
gion pressure is selected as the datum. If the inlet The long dimension of the elemental area shall
region pressure is not thedatum, then the inlet ve- align with the long dimension of the duct cross
locity pressure is zero and the inlet totaland inlet section.
static pressures are each equal to the inlet region The intent of this specification is to make the
pressure (seeFig. 4.4). However, if such fans are elemental areas closely geometrically similar to the
equipped withinlet boxes, the flow can be expected duct cross section. [See Ref. (7) and Fig. 4.1.1
to be quite uniforma t the entrance to the inlet box, For measurement planes of circular cross section,
particularly if equipped withan inlet bell, and this there shall be a minimum of eight equally spaced
may be the optimum location for a velocity traverse radial traverse lines(8 radii or4 diameters), andthe
to determine the flow rate. distance between adjacent points on any radial line
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ANSVASME PTC 11 -1 984

FANS AN AMERICAN NATIONAL STANDARD

Ports for probe insertion

(Use both sides for long insertions.)

clear obstructions.
1
Traverse plane

locations

GENERAL NOTE:
See Par. 4.2.4 for specifications.

FIG. 4.1 SAMPLING POINT DETAILS (RECTANGULAR DUCT)

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AN AMERICAN NATIONALSTANDARD FANS

Preferred
locations

Location of Traverse Points in a Circular Duct

From: a, = -
2 a =probe penetration external
Maximum offset
to clear
u = number ofobstructions
traverse
points each radius
n =point number

Preferred
Traverse
Zones Along Each
Radius
where
r, = depth inradial
direction
d, = D"a,
e = number of radial
traverse lines

FIG. 4.2 SAMPLING POINT DETAILS (CIRCULAR DUCT)

22

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ANSIIASME PTC 11-1 984

FANS ANAMERICANNATIONALSTANDARD

shall not be less than 0.5 ft (0.15 m). (It may be calculation of results, but for monitoring opera-
necessary to increase the number of radial linesto tional steadiness.
meet this requirement.) Refer to Fig. 4.2. Note that the absolute pressure may varysignifi-
cantly betweentwo locations, both of whichare in
the vicinity of the test. For instance, if the fan is
4.2.5 Orientation of Traverse Ports. Yaw and pitch installed in a room and the air is drawn through
are the twoangles necessary to orient the velocity silencers or heaters, the pressure in the room will
vector with respecttothe nominal direction of flow be lower than that outside. See Fig. 4.4.
(normal to themeasurement plane). It is desirable,
when measuring both yaw and pitch, to measure
the larger angleby rotating the probe as explained 4.3.5 Operation. The method ofusing a barometer
in Par. 4.9.5. For this reason, the traverse ports is amply covered in the section of barometers in
should be located in the duct wall or walls which PTC 19.2.
will orient the probes accordingly.
For measurement planes of circularcross section,
the traverse ports should be oriented so that the
probe stem will be inserted radially. 4.4 TEMPERATURE
For measurement planes of rectangular cross
section, the traverse portsshouldgenerallybe 4.4.1 Instruments. Gas temperatures shall be mea-
oriented so that the probe stem i s parallel to thefan sured using thermometers or other temperature
shaft. This is particularly appropriate for inletmea- measuring systems as appropriate. Ordinaryliquid-
surements on either axial or centrifugal fans with in-glass thermometers are generally preferred for
inlet boxes. It is also appropriate for outlet
measure- ambient air measurements.Thermocouple systems
ments on centrifugal fans unless the geometry of are generally preferredfor measurements in ducts.
the diffuser would suggest otherwise. In any case,
the parties shouldagree in advance to the orienta-
4.4.2 Accuracy. The temperature measuring system
tion of the traverse ports. Refer to Figs. 4.3(a) and
shall have a demonstrated accuracy of -t-2.0°F
4.3(b). (&I.Oo C). Readingsshall be corrected for emergent
Stem, reference junction temperature, and any
other condition which mightaffect the reading as
4.3 ATMOSPHERIC PRESSURE noted in the appropriate paragraphs of PTC 19.3.
4.3.1 Instruments. The atmospheric pressure shall
be measured with a barometer. A Fortintype 4.4.3 Calibration. Instruments shall be calibrated in
barometer i s generally preferred, but an aneroid accordance withthe chapter on calibrationof
type can be acceptable. instruments in PTC 19.3.

4.3.2 Accuracy. The barometer shall have a demon-

4.4.4 Number of Readings. Temperature measure-
strated accuracy of plus or minus 0.05 in. Hg (170
ments shall be made a t each traverse point foreach
Pa).
traverse plane. Temperatures can be measured
Readings shall be corrected for temperatureand
simultaneously with pressures if the thermocouple
gravity according to the procedures given in PTC
is attached to thepressure probe so that it does not
19.2 in the section on barometers.
interfere with other measurements.
If the fan handles ambient air, the air tempera-
4.3.3 Calibration. The barometer shall becali- ture shall be measured in the test vicinity at the
brated in accordance with the section on barom- beginningofthetestandevery15minuntilthetest
eter calibration in PTC 19.2. is completed. These measurements are used to
monitor the operational steadiness andto calculate
the results.
4.3.4 Number of Readings. Measurements shall be
made in thetest vicinity at the beginning of the
test
and repeated every 15 min until the test is com- 4.4.5 Operation. The operation of various temper-
pleted. These readings shall be used not only for ature measuringsystems shall conform toPTC 19.3.
23

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AN AMERICAN NATIONAL STANDARD FANS

Outlet traverse
plane421
I

Z 1
I 1
l /I t +I )
T
view Plan
Inlet traverse
plane411 +
V A @ i
+
I

Side Elevation
O

"lx = v c o s W cos @
v* = v cos
Probe Axis Parallel to Fan Shaft

FIG. 4.3(a) PROBE ORIENTATION - CENTRIFUGAL FANS

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 ANSIIASME PTC 11 -1 984
FANS ANAMERICANNATIONALSTANDARD

I'
+-+-t-t, o o o o c

8
5
5
h

. . .

25

.,
4 ;
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 , ASME PTC*LL 8 4 N 0 7 5 7 b 7 0 0053302 3

ANSVASME PTC 11 -1984

AN AMERICANNATIONALSTANDARD FANS

Open to
Gage pressure
in room P fan room

PS1 = Pt1 7 Open to atmosphere a

Total pressure probe

+
Air entry

-+ -
Discharge to boiler, etc.

Open to

Open to atmosphere

Gage pressure
in room
PS1 = Pt1

FIG. 4.4 FAN ROOM PRESSURE

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ANSIIASME PTC 1 1-1 984

FANS ANAMERICANNATIONALSTANDARD

4.5 MOISTURE 4.6.2 Accuracy. The gas compositionmeasuring

system shall have a demonstrated accuracy of 0.1%
4.5.1 Instruments. The moisturecontentof am-
by volume for each majorconstituent (e.g., 5%
bient air shall be measured using a psychrometer or
+0.1% for oxygen).
other humidity measuring system. A simple sling
psychrometer is generally preferred.
The moisturecontent of other gases shall be 4.6.3 Calibration. The various elements of the gas
measured using a condensation/desiccation sam- composition measuring system shall be calibrated
pling train or other moisture measuring system. against appropriate standards. Certified standard
Stoichiometric methods can also be used in some gas samples are available commercially.
cases. The condensation/desiccation method is
generally preferredbecause it does not require fuel
sampling and analysis. 4.6.4 Number of Readings. Gas composition mea-
surements shall be made at every other pointusing
every other port for at least one traverse plane. The
4.5.2 Accuracy. The humidity measuring system samples for any port can be mixed before mea-
shall have a demonstrated accuracy of 0.001 mass surement. Even this requirementcan be reduced to
units of water vapor per unit mass of dry gas. a single point sample if the parties agree that the
preliminary test shows the distribution ofgas com-
4.5.3 Calibration. The variouselements in the mois- position is sufficiently uniform.
ture measuring system shall each be calibrated
according to the procedure for that elementin the 4.6.5 Operation. Operation of flue and exhaust gas
appropriate PTC 19 Supplement. analysis systems shall conform to PTC 19.10.

4.5.4 Number of Readings. If the fan handles am-

bient air, the ambient air measurements shall be 4.7
PRESSURE SENSING
made in thetest vicinity a t the beginning ofthe test
Point values of pressure (velocity, and total or
and repeated every 15 min until the test is com-
static pressure) shall be measured using a probe
pleted. These readings shall be used to monitor
that can be positioned at the appropriate pointsby
operational steadinessand to calculate results.
insertion throughone or more ports as required. A
Moisture measurements in other gases shall be
probe capable of measuring static pressure, total
made at every other point using every other port
pressure, their differential, yaw, and pitch is pre-
for at least one traverse plane. The samples from
ferred. A probe with only yaw measuring capability
any port can be mixed before measurement. Even
can only be used if a preliminary test gives good
this requirement can be reduced to a single point
evidence that pitch does not exceed 5 deg. A
sample if the parties agree that the preliminary test
nondirectional probemay only be used where the
shows the distribution of moisture is sufficiently
preliminary test gives good evidence that neither
uniform.
yaw nor pitch exceeds 5 deg.

4.5.5 Operation. The operation of a moisture sam-

4.7.1 Instruments. Nondirectional probes include
pling train shall conform to the Federal Register,
Pitot-static tubes and Stauschiebe tubes. The latter
Vol. 42, No. 160, August 18, 1977.
are also called type S or forward-reverse tubes.
Direction finding probes include the Fechheimer
probe which has two holes and is capable of
4.6 CAS COMPOSITION
determining yaw anglesand static pressure only. A
4.6.1 Instruments. The composition of air can gen- three-hole version of the Fechheimer probe, also
erally be assumed to be that of normal atmospheric called a three-hole cylindrical yaw probe, can be
air and measurements need not be made. used to determine total pressure (and therefore
The composition of other gases shall be mea- indicated velocity pressure) as well as the static
sured by using a sampling train containing a gas pressure and yaw. See Fig. 4.5. A five-hole probeis
analysissystem. The Orsat apparatus is generally generally required to determine pitch angles as
preferred for flue gas measurements. well as the various pressures and yaw angles. See
27

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AN AMERICANNATIONALSTANDARD FANS

Yaw angle -

Static
pressure

Null balance
pressure
GENERAL NOTE:
U-tubes are shown but inclined manometers
or other transducers can be used.

FIG. 4.5 FECHHEIMER PROBE

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ANSVASME PTC 11 -1984

FANS ANAMERICANNATIONALSTANDARD

Flow

4
c

Null balance
pressure

Pitch
pressure

Velocity
GENERAL NOTE: pressure
U-tubes are shown but inclined manometers
or other transducers can be used4 Static
d*
pressure

FIG. 4.6 FIVE-HOLE PROBE

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ANSI/ASME PTC 1 1 -1 984

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Fig. 4.6. Probes with wedge shapes where the holes cated velocity pressure pvi, can each be recorded
are located are slightly preferred over probes with for each probe.Whencalibratingdirectional
cylindrical shapes throughout, because they are probes, the static pressurefrom each static pressure
easier to null-balance. See Par. 4.9.5. If more than holeshouldbe observedand any differences
one probe is present in the measuring plane, the noted. The static pressure hole that is used to obtain
total blockage of all probes shall not exceed 5% of indicated velocity pressure during the calibration
the duct cross-sectional area. shouldbe noted and the same hole used for
subsequent tests.
Probe calibration shall be expressed in terms of a
4.7.2 Accuracy. Refer to Par.4.8 for accuracy of
probe total pressure coefficient K , and a probe
pressure readings and to Par.4.9 for accuracy of
velocity pressure coefficient K v . The probe total
angularity readings.
pressure coefficient is calculated from thetest data
by
4.7.3 ProbeCalibration. All probes except Pitot-
statictubes shall be calibrated. Pitot-static tubes are (Ptilref
K, = -
considered primary instruments and need not be (Pti)tert
calibrated provided they are maintained in the
specified condition described in Ref. (4). The cali- The probe velocity pressure coefficient is calcu-
bration procedures specified in this paragraph lated from the test data by
apply to pressure measurementonly. Calibrationof
probes for direction sensing is usually carried out
simultaneously with calibration for pressure. See
Par. 4.9.3 for calibration procedures for direction
sensing.
Probe calibration may be carried out in a free
stream nozzle jet (see Fig. 4.7) or a closed wind
tunnel. Ineither case, the probeblockage shall be where
less than 5% of the cross-sectional area. Preferably,
the probeblockage should beas small as possible.
The flow should be adjusted to produce at least
eight equally spaced calibration points.
The calibrationreference may be a standard and
Pitot-static tube (preferred) or a previously cali-
brated reference probe of anothertype. The block-
age of the reference probe should be as small as
possible. Inno case shall the blockage ofthe
reference probe exceed 5% of the cross-sectional NOTE: It is recognized that C, is usually not known to a high
area. degree of accuracy. Lacking specific information, C, = 1.2 for
probes of cylindrical shape. For a closed wind tunnel, p will be
The reference probe and the test probe shall positive; for a free jet, p will be negative.
each be mountedso that they can be placed in the
stream alternately and their positions in thestream The equation for K v includes a correction for
will be the same and firmly held. When calibrating probe blockage derived fromthe analysis pre-
directional probes, the probeshall be aligned with sented in Refs. (11)and (12).If thereference probe is
the stream in order toeliminate yaw according to a Pitot-static tube, Kv, ref = 1 and the blockage of
the null-balance principle described in Par. 4.9.5. both the reference probe and the test probe is
Staticpressure indication shall be from the ap- negligible (S& < 0.0005), the equation for K v
propriate static pressure hole(s) of the reference assumes the simplified form
probe and test probe and not fromwall taps (wind
tunnel) nor shall it be assumed equal to ambient
pressure (free jet). The test probe and reference
probe shall be connectedto appropriate indicators
so that the indicated static pressure psi,indicated The probetotal pressure coefficient and the
total pressure pti, and their differential, the indi- probe velocity pressure coefficient shall be repre-

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ANSVASME PTC 11-1984

FANS
AN AMERICAN NATIONAL STANDARD

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ANAMERICANNATIONALSTANDARD FANS.

sented as functions of Reynolds Number for non- fluid, gas column balancing effect,or any change in
directional and three-hole probesand as functions length of thegraduated scale due to temperature.
of pitch pressure coefficient, C,, and Reynolds However, correctionsmay be omitted fortempera-
Number for five-hole probes. See Par. 4.1.2 regard- ture changes less than I O O F (5°C)from calibration
ing calibration function. and elevation changes less than 5000 ft (1500 m).
Calibrated probes should be handled with care
because large scratches or nicks near the pressure
taps will invalidate the calibration. 4.8.3Calibration. Pressure indicating instruments
shall be calibrated against a suitable standard. For
pressures from O to IO in.wg (O to 2.5 kPa),
4.7.4 Number of Readings. Pressure measurements calibration shall be against a water-filled hook
shall be made at each traverse pointfor each gage of the micrometertype or a precision micro-
traverse plane. The indicated velocitypressure and manometer. When the pressure i s above 10 in. wg
either the total pressure or thestatic pressure shall (2.5 kPa), calibration shall be against a water-filled
be measured, The remaining pressure can be de- hook gage of the micrometer type, a precision
termined arithmetically. micromanometer, or water-filled U-tube.Pressure
Pressures can be obtained at two or moreloca- indicating instruments should preferably be cali-
tions, simultaneously, by using two or more probes brated in place, but t h e parties mayagree to a
as appropriate. It may be desirable to traverse both remote calibration in a more suitable laboratory
inlet boxes of a double inlet fan and to traverse environment. In the lattercase, extreme care should
from both sides of the outlet, all simultaneously. be taken to mount the pressure indicating instru-
This would require four probes and four probe ment in exactly the same manner for calibration as
crews, but it would significantly reduce the total it i s mounted forthe test. Calibration pointsshall be
elapsed time required for thetest, selected to fall a t both ends of the expected range
and at sufficientintermediatepoints s o that no
4.7.5 Operation. Refer to Pars. 4.8.5 and 4.9.5. readingwill be more than 9.25 in. wg (60 Pa)
removedfrom a calibrationpointforinclined
manometers or morethan 1in. wg(250 Pa) removed
for U-tube manometers.
4.8 PRESSURE INDICATING
4.8.1 Instrunlents. Manometers or other pressure 4.8.4 Number of Readings, Pressure measuring
indicating systems shall be connected to the ap- instruments shall be read at each position of the
propriate taps of the pressure sensing probes to probe as outlined in Par. 4.7.4. Since pressures are
measure point values of pressure. A five-hole seldom strictly steady, the pressure indicated on
probe requires one indicator for velocity pressure, any instrument will fluctuate with time.In order to
one indicator for static pressure or total pressure, obtain a reading, either the instrument shall be
and additionalindicatorsfornulling and pitch damped orthe readings shall be averaged in a
determination. (See Par. 4.9 for the latter.) A three- suitable manner. Averaging can be accomplished
hole probe requires the same indicators, except mentally, i f the fluctuationsare small and regular. If
that forpitchdetermination. A nondirectional the fluctuations are large and irregular, more so-
probe requires indicatorsonly forvelocity pressure phisticated methods shall be used. I t is possible to
and either staticor totalpressure. Inclinéd manom- obtain a temporal average electronically when an
eters are generally preferred, but U-tube manom- electrical pressure transducer i s the primary ele-
eters and other indicators are acceptable if they ment. Even though the spatial average velocity i s
meet the following specifications. obtained from the square roots of the temporal
average velocity pressures, it i s not proper totake
the square root of the raw data before temporal
4.8.2 Accuracy. Pressure measuringsystems includ- averaging as this may introduce a bias into the
ing the sensor and theindicator shall have a average values [Ref. (9)].
demonstrated accuracy of "1% of the reading or
0.01 in. wg (2.5 Pa), whichever is larger. Readings
shall be corrected for any difference from calibra- 4.8.5 Operation. For many oftheprinciplesof
tion conditions in specific weight of manbmeter operation, refer to PTC 19.2. Refer to Figs. 4.5 and

32

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ASME P T C * L l 8 4 W O 7 5 7 6 7 00 0 5 3 3 0 7 b m
ANSVASME PTC 11 -1984
FANS ANAMERICANNATIONALSTANDARD

4.6 for the proper hose connecting arrangements 4.9.4 Number of Readings. Yaw and pitch angles
for probes and indicators. Precautions should be shall be measured at each traverse point for each
taken to protect the indicator from the effects of traverse plane. This is the same requirement as
wind, sun, and boiler radiant heat. Periodically for pressures which shouldbe measuredsimultane-
during the test, probes, hoses,and indicatorsshould ously.
be checked for leaks or plugging. Plugging can
result from eitherparticulate buildup in the probe
or condensation in a portion of thesystem. 4.9.5 Operation. In operation, a five-hole probe i s
Indicators used for static or total pressure mea-
inserted in the proper port the to proper depth for
surement have one tap open toatmosphere. If the
eachtraverse point. The probe shouldbe rigid
indicator is not located in thesame atmosphere as
enough over its inserted lengthto avoid any droop
the barometer, an additional measurement to de-
beyond the permissible amount as noted in Par.
termine the difference in pressure is required. See
4.2.4. The reference line on the probe should be
Fig. 4.4.
used to orient the probe insuch a way that when
the total pressure hole i s pointing upstream per-
pendicular to the measuring plane, the indicated
yaw angle is zero. The probe is then rotated about
4.9 YAW A N D PITCH i t s own axis until a null balance is obtained across
4.9.1 Instruments. Yaw and pitch angles shall be the taps of the static pressure holes. The angle of
measured using a directional probe equipped with probe rotation from the zero yaw reference direc-
suitable indicating devices. A five-hole probe is tion is measured with an appropriate indicator and
preferred as noted inPar. 4.7.1. A three-hole probe is reported as the yaw angle. Without changing the
may be suitable in some cases. Sw Figs. 4.5 and 4.6. angularity of the probe, the pressure difference
across the taps for the fourth and fifth holes shall
also be recordedand used withtheindicated
4.9.2 Accuracy. The yaw and pitch measuring sys- velocity pressure and the pitchpressure coefficient
tem shall have a demonstrated accuracy of f 2 deg. to determine pitch angle. Measurements of indi-
each. cated velocity pressure and static pressure or indi-
cated velocity pressure and total pressure as out-
lined inPar. 4.7.4 shall be recorded with the probe
4.9.3 Calibration. A reference line shall be scribed
in the proper null-balance position, (Note that a
on the probe at the time ofcalibration for pressure
null balance can be obtained at fourdifferent
response.The protractor scale withwhichthe
positions but only one is correct. Incorrect null
probe is then equippedcan be checked against any
positions usually correspond to negative velocity
high-qualityprotractor used as a reference. As
pressures.)
noted below, the protractor arrangement is only Athree-holeprobe is operated in a similar
used to measure yaw. manner exceptthat the pitchpressure difference is
Pitch anglesare determinedfrom a pressure
omitted.
measurement obtained with a pressure indicator
connected across the fourth and fifth holes of a
five-hole probe. Calibration for pitch can be per-
formed in a free stream nozzle jet or in a wind
tunnel, The probe shall be precisionaligned at
4.10 ROTATIONAL SPEED
various pitch anglesand the pressure difference
across the taps forthefourth and fifth holes 4.10.1 Instruments. The speed of the fan shall be
recorded. The flow should be set at several values measured with a speed-measuringsystem. An elec-
for each position of the probe and each time the tronic counteractuated bya magnetic pulse gener-
pressure difference across the yaw taps should be atoror photoelectricpickup is preferred. Slip
nulled. counting withstroboscopic light may be acceptable
Acalibrationfunctionwhich represents pitch for speeds close to line frequency synchronous
angle as a function of pitchpressure coefficient, C, speeds. Hand tachometers, mechanical revolution
(= pitch pressure differencehdicated velocity pres- counters,andvibrating-reedtachometers are
sure) and Reynolds Number is derived. See'Fig. 4.8. unacceptable.

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 i

1.25
4 for IRq

4 for IRP2

4 for iRP3
1.20 --$zz 40
-\ A\ -C 4

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z
.g
5 1.15

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$
0

G
I2
I
1.10
‘i=
1.05
‘I4
1.00

-1.0 - 0.8 - 0.6 - 0.4 - 0.2 0 0.2 0.4 0.6 0.8 1.0

CQ, - Pitch Pressure Coefficient

GENERAL NOTE:
Actual calibration curves may
exhibit discontinuities.

FIG. 4.8 TYPICAL CALIBRATION CURVES FOR A FIVE-HOLE PROBE

 ANSVASME PTC 1 1 -1 984
FANS AN AMERICANNATIONALSTANDARD

4,10.2 Accuracy. The speed-measuringsystemshall beforehand to the method of calibration and the
have a demonstrated accuracy of 50.1%or 5 1 rpm, expected accuracy. (See Section 5 of PTC 19.7-
whichever is smaller. 1980.)
Since the temperature rise through a fan is
generally not large enough to permit accurate
4.10,3 Calibration. Speed-measuring instruments
measurementand since heat transfer losses through
shall be calibrated against the line frequency of a
the casingare indeterminate, the heat balance
suitable major power circuit or other frequency
method is not acceptable for determiningfan input
standard.
power.

4.10.4 Number of Readings. Fan speed shall be

4.11.2 Accuracy. The input-power-measuring sys-
measured at the beginning of the test andevery 15
tem shall have a demonstrated accuracy of 51%.
min until the conclusion of thetest. These readings
shall be used to monitor operational steadiness as
well as for calculations. 4.11.3 Calibration. A torque meter shall be cal-
ibratedin accordance withtheprovisionsof
PTC 19.7.
4.10.5 Operation. The electronic counter should
be equipped with a digital readout and may be The drivetraininthecontextofthisCode
includes the driver, whether it be electricmotor or
equippedwith a recorderand an automatic
steam turbineorotherprime mover, and any
averager.
With the slip method, the shaft must be marked intermediate elements,such as gear boxes and
with a reference line or other mark that is easily
variable speeddrives. The drivetrain may be
visibleunderstroboscopic light flashing at line calibrated as a unit or the driver and any inter-
mediate elements may be separately calibrated.
frequency. The mark will appear to slowly rotate
Calibration procedures as given in the following
opposite shaft rotation and permit visual observa-
documents shall be followed as appropriate.
tion of the slip frequency. A stopwatch shall be
used to measure the time for at leastten rotations of ANSIAEEE 112-78 Test Procedure for Polyphase
the mark. Average slipfrequency is derived by Induction Motors and
dividing the total number markof rotations by the Generators
measured time interval for which the counts were IEEE 115-65 Test Procedure For
made. Synchronous Machines
SeePTC 19.13 for further information on the IEEE 113-72 Test Code for Direct Current
measurement of rotary speed, Machines With Supplement
11 3A-76
ASME PTC 6s Simplified Procedures for
4.11 INPUT POWER Routine Performance Tests of
4.11.1 Instruments. The fan input power shalr be Steam Turbines
derived frommeasurements of torque with a torque ASME PTC 17 Reciprocating Internal
meter, or measurements of electrical input when a Combustion Engines
calibrated electric motor is used, or other suitable ASME PTC 18 Hydraulic Prime Movers
measurements if the fan is driven by some other ASME PTC 19.7 Measurement of Shaft Power
calibrated prime mover and drive train. Both the
ASME PTC 22 Gas Turbine Power Plants
torque meter and the calibrated prime mover
Calibration shall be performed under specified
measurements qualify as preferred methods. If a
torque meter cannot be used and if the drive trainis operating conditionsand a range of loads sufficient
to cover the anticipated test conditions,
not calibrated prior toinstallation, the parties to the
test must agree upon a method of estimating the
drive trainlosses. Also, it must be noted that various 4.11.4 Number of Readings. Torque or electrical
methods and procedures for calibrating the drive input shall be measured at the start of the test and at
train may result in accuracies which are unaccept- least every 15 min until the conclusion of the test.
able for this Code. The parties to the test and the These readings shall be used to monitor opera-
party responsible for the calibration mustagree tional steadiness as well as for calculations.
35

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TABLE4.1 SUMMARY OF INSTRUMENTATION REQUIREMENTS

Frequency of Paragraph
Instrument Measurement Readings Accuracy Reference No.

Atmospheric Barometer f0.05 in. Hg 15 min PTC 19.2 4.3

pressure H 7 0 Pa

Temperature Thermometer or t2.0° F Each traverse PTC 79.3 4.4

thermocouple +.I.O"C point

Moisture Psychrometer or 0.001 Ibm/lbm gas Air 15 min PTC 19.10 4.5
condensation/ 0.001 kg/kg gas Gas alternate PTC 38 4.5
desiccation traverse points

Gas analysis Orsat or 0.1% by volume Alternate PTC 19.10 4.6

electronic traverse
analyzers points

Pressure Manometer or Larger of Each traverse PTC 19.2 4.8

pressure indicator f1.0% or point
k0,I in. wg
f 2 . 5 Pa

Yaw angle Protractor +2.0 degree Each traverse ... 4.9

point

Pitch angle (See Pressure) ... Each traverse ... 4.8 and 4.9
point

Speed Magnetic puke Smaller of 15 min PTC 19.13 4.10

Fiber optic +0.1% or +-I rpm
or slip

Power Torque meter or *1.0% 15 min PTC 19.7 4.11

calibrated drive PTC 19.6

4.11.5 Operation. Operation of prime movers is full-scale accuracy of 0.5% or better. They shall be
covered in thevarious Standards listedin Par.4.11.3. used in the same position as rated (usually hori-
Operation of the instruments for measuring the zontal). Care should be taken to maintain instru-
output of these prime movers is covered in various ments a t a uniform and constant temperature near
supplements on instruments and apparatus. Elec- the calibration temperature; otherwise, correc-
trical instrumentsshall conform to ANSI C 39.1, tions shall be made according to manufacturer's
Requirements for Analog Indicating Instruments. A instructions regarding lead wires, waveform, etc.
wattmeter and voltmeter or an ammeter, volt- The preferred location for taking electrical mea-
meter, and power factor meter may be used to- surements i s at the terminals of the motor. Ifthis i s
gether with the necessary instrument transformers. not possible, then allowance shall be made for the
Refer to PTC 19.6, Electrical Measurements in drop in potential between the point of measure-
Power Circuits, for instructions. Meter ranges and ment and the motorterminals. Care shallbe taken
transformer ratio shall be such as to produce t o measure motor power onlyand not includeany
readings aboveY 3 full scale. Instruments shall have auxiliary's power.
36

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FANS AN AMERICANNATIONALSTANDARD

SECTION 5 - CALCULATIONS

5.1 GENERAL CONSIDERATIONS

The results of the test shall be calculated in accordance with the appropriate paragraphs of this
Section and any prior agreement reached by the parties regarding computation of results. The
following paragraphs are intended to cover all possible cases but it i s not necessary to use every
paragraph for any particular case. Forinstance, it is not necessary to refer to the paragraphson products
ofcombustion if the test gas is air. Similarly, only the paragraphon computing power which
corresponds to the methodof power measurement shall be used. Various other calculations may be
omitted depending onwhether mass flow rate and specific energy or volumeflow rate andfan total
pressure are used to express fan performance. The datato be used in the calculations are the measured
values of pressure and temperature at various planes, the fan input power measurements, various
geometric information(primarilyduct areas at measurement planes), and information used to
determine gas composition.

5.1.1 Calibration Corrections. Temporal averaging shall be performed prior to correcting for calibra-
tions. Calibration correctionsshall be applied to individual readings before spatial averaging or other
calculations.

5.1.2 Average Values. Recognizing that nonuniform velocity distribution and temperature or com-
position stratification are normal on large fans, the appropriate volume-flow-weighted ormass-flow-
weighted average values at the traverse planes must be used for determinations of fan performance
[Ref. (IO)].

5.2 CORRECTION OF TRAVERSE DATA

Difficulties arise in employingtraverse data in calculationsas these datausually must be corrected for
probe calibration and possibly for blockage and compressibility as well. The probe calibration coef-
ficients K , and Kv are generally functions of theprobe Reynolds Number I R p , which i s determined by
actual gas velocity V, density p, and viscosity p a t the probe location. They are alsoslightly dependent
upon specific heat ratio k . As these four quantities are determined only from the measurements
themselves, an iteration procedure may be necessary. Such a procedure would be as follows.
(a) Select provisional values of Ky, Kvj and k (see Par. 5.2.1).
(b) Correct the traverse readings for calibration and, if necessary, probe blockage and compres-
sibility (see Par. 5.2.2).
(c) Proceed with calculations.
( d ) After determining gas composition [see Par. 5.3), densities (see Par. 5.4), and velocities (see Par,
5.5.1) at all points in a traverse plane, calculate Reynolds Number (see Par. 5.2.2) at all points and
determine new values of Ktj and Kvj,
(e) If new values of Ktjand K,jare significantly differentfrom the old values, then theprocess must be
repeated.
The probe calibration coefficientsare alsoafunction of pitch pressure coefficient (C,&; however, this
dependency does not affect the iteration process.
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5.2.1 Guidelines for Initial Estimation of Probe Coefficient. To begin calculations, initial values of KV
and KVj must be selected. The selection of an appropriate value makes the calculation procedure
converge more rapidly, often making iterationunnecessary. Followingare guidelines to helpthe initial
selection of Ktj and Kvj.
(a) For Pitot-static probe, KV and Kvj = 1.0 and need not be changed.
(b) For other probes, the K y and Kvj versus R, curves should berelatively flat in the range of interest,
hence any reasonable first estimates of Ktj and Kvj-should produce satisfactory results. Thefollowing
ideas are suggested.
(7) Select the values of KV and Kvj a t the middle of the range of calibration data, or
(2) Use an average Ky and Kvj value based on the calibration data, or
(3) Estimate IR, from specified fan conditions and use corresponding K,j and KVj values, or
(4) Estimate IR, from a typical point in the traverse data and use the corresponding K,j and KVj
values.

5.2.2 Correction for Probe Calibration,Probe Blockage, and/orthe Effectsof Compressibility.

Measured values from traverses aret i , pviand psi or pli.The remaining pressure canbe calculated from
pti = psi t pvi.Corrected values, (subscriptj) at eachpoint shall be obtained from themeasured values,
(subscript i ) at that point and probe coefficients KV and Kvj using

p I]. = / ( I.l P t l. (5.2-1)

(5.2-2)

p S]. = / ( 1,Pll
. . - K .V l C P V i or

(5.2-3)

(5.2-4)

( p v j = O for reverse flow) and (5.2-5)

Tsj= Ti/(l + E ~ ) where (Ti = t i + C,) (5.2-6)

ßi is used to correct for probeblockage and is calculated by

(5.2-7)

In these equations, (I - E,) and (1 + E ~ are

) compressibility corrections and are calculated by

(5.2-8)

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FANS AN AMERICAN NATIONAL STANDARD

and

(5.2-9)

provided that (Kvjcpv;/psaj)

does not exceed 0.1. See Par. 3.3.6.
NOTE: The recovery factorof the temperature sensor is assumed to be 0.85 [Ref. (13)].

5.3 GAS COMPOSITION

For the purposes of thisCode, it i s sufficient to use a uniform gas composition and uniform
values of
molecular weight, specific heats, and viscosity to characterize any particular plane,These valuesshall
be determined by arithmeticaveraging of gas composition data and the use of arithmeticaverages of
measured temperatures in theplane in question where temperaturesare needed to determine the
appropriate gas properties.

5.3.1 Arithmetic Averages of Compositionand PropertyData. The average volumefractionof

constituent ( X ) , at plane x shall be calculated from the pointvalue ( X ) j using

(5.3-1)

The averagetemperature T, at plane x (to be used only forpurposes of defining gas composition and
properties) shall be calculated from the point values using 5
~

1 "
T,=-
n
ET/ (5.3-2)

5.3.2 MolecularWeightand Specific Humidity. The molecular weight of dry air is 28.965. The
molecular weight of drygas Md, shall be calculated from the average volume fractions ( X ) , using

M d g = 44.01(C02) + 28.02(N2) + 28.01(CO) + 32.00(02) + * (5.3-3)

The molecular weight of moist gas M, at plane x shall be calculatedfrom

1
M, = (5.3-4)
1
S
18.02(1 +S)
+hfdg(l + S)

Thespecific humiditys ofmoist atmosphericaircan be calculated from thewet-buIbt,and dry-bulbtd

temperature measurements using

(5.3-5)

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and

(5.3-6)

These equations can alsobe used to calculate the specific humidity of any other wet gas, provided
reliable wet-bulb and dry-bulb temperature measurements can be made. Refer to the ASME Steam
Tables for values of hf,, h,, hf, and pe. Refer to Eq. (5.3-12) for thecalculation ofthe specific heat of the
dry gases (Cpdg).
In the event a condensation/desiccation method is used to measure moisture content,a calculation
method appropriate to the measurement method shall be used.

5.3.3 Specific Heat [Ref. (14)]. The specific heatof dry air cpairshall be computed from

XO
I 4
- -+
1.253
83.76
3.087
cP air = C5[0.343 -- (5.3-7)
(C3T)1/2 (C3T) (c3T)2

The specific heat of the dry specific heats cpxusing

gas cpdgshallbe computed from the component

6.53 X O
I 31.4 X I O 6
16.2 - +-
T) (C, (C3TI2
cpco2 = c5 (5.3-8)
44.01

1530 172
11.515 - -+ -
(C3T)”2 (C37.1
cpo2 = c5 (5.3-9)
32.0

3.47 X O
I 31.16 X O
I6
9.47 - +
(C3TI2 (C3T)
CpN2= c5 (5.3-10)
28.02

3.29 X O
I 31.07 X O
I 6
9.46 -
(C3T)
+ (C3TI2
cpco = c5 (5.3-11)
28.01

(5.3-12)

The specific heatof thewater vapor c ~ shall

H be~ calculated
~ from

597 7500
19.86 - ~ + -
(C3T)’lZ (C3T)
cpn2o = C5
18 (5.3-13)

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ANSI/ASME PTC 1 1 -1 984

FANS AN AMERICANNATIONALSTANDARD

The specific heat of moist air cpmashall b e calculated from

- 1 S
%ma - cpair l+s C ~ H ~ o l+s (5.3-14)

gas cpwsshall b e calculated from

The specific heat of the wet

I S
%w = l+s + ‘pH20 G (5.3-15)

5.3.4 Specific Cas Constant and Specific Heat Ratios. The specific gas constant R shall be calculated
from the molecular weight M, and the universal constantR, using

(5.3-16)

The specific heat ratio k is

(5.3-17)

5.3.5 Viscosity [Ref (15)]. The viscosity of air pairshall be calculated from

1 O.874 ( C3T )3’2

Pair = C4 x IO-^ (5.3-18)
c37 + 199

The viscosities of t h e gas components px shall be calculatedfrom

12.721 (C3T)3/2
= c4 x 10-~ (5.3-19)
“02
+
(c3r 515.04)

10.86 (C3T)3’2
PC0 = c4 x IO-^ (5.3-20)
+
(C3T 214.72)

10.75 (C3T)3/2
= c4 x 10” (5.3-21)
+
(C3T 204.67)

13.11 (C3T)3/2
x
Po, = c4
+
(C,T 238.54) (5.3-22)

12.03 (C3T)3/2
= c4 x IO-^ (5.3-23)
PH20
+
(C3T 987.4)

The viscosity of moist air pma shall b e calculated from

(5.3-24)

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The viscosity of the moist gas pingshall be calculated from

[m(CO,)+ J3200(0,)-t &äõT (CO)

-[ -1)
+ m (N,) + + d.18.02
* *
sMdg
(5.3-25)
18.02

5.4 DENSITY
5.4.1 Atmospheric Air. The density of atmospheric air in the vicinityof the test shall be determined
from measurementsof dry-bulb temperature t d , wet-bulb temperature tw,and barometric pressurepb
using Fig. 5.1 or a curve fit similar to the following.The saturated vapor pressure pe and the partial
pressure pp of water vapor in air can be determined from

pe = csti ~ + + cBt
~ , ~ (5.4-1)

for air between 4OoF and 100°F (SOC and 4OoC), and

(5.4-2)

Thedensity of the atmospheric air-vapor mixture po shall be calculated using the ideal gas
relationship

CIO(Pb - 0.378Pp)
Po = (5.4-3)
R (rd + cl)
The point values of density shall then be calculated from

(5.4-4)

5.4.2 Cas Products of Combustion. The density of products of combustion pj at each point shall be
calculated from absolute pressure psa,absolute temperature Tsj, and specific gas constant R using the
ideal gas relationship

(5.4-5)

5.5 FLUID VELOCITY

5.5.1 Point Velocities. The velocity Vj at each point ina traverse plane shall be calculated from

vj = C I 2 6 (5.5-1)

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FANS AN AMERICAN NATIONAL STANDARD

Wet-Bulb Depression, OF

Air Density - Ibrn/ft3

FIG. 5.1 PSYCHROMETRIC DENSITY CHART

(Reprinted fromStandard 51-75 by permissionof the American Societyof
Heating, Refrigerating and Air-Conditioning
Engineers, Inc.)

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5.5.2 Correction for Probe Calibration Coefficient. For each point j , calculate the probe Reynolds
Number lR,j using

(5.5-2)

Using the probe calibration, obtain new values of KV and Kvj at each point. Recompute p t j , Kvjc, psi,
psaj,pvj, and T, at each point using new Ktj and KVj in Eqs. (5.2-1), (5.2-2), (5.2-3), (5.2-4), (5.2-5), and
(5.2-6). Recompute velocityat eachpoint Vi using newpvj in Eq. (5.5-1). At any point at which thevalue
of K y and Kvi has been changed bymore than0.1%, it will be necessary to repeat the calculations of Pars.
5.2,5.3,5.4, and 5.5 using corrected values of measured pressuresand temperatures. If no points have
Ktj and Kvj changed by morethan 0.1%, calculations may proceed using the latest valuesof Vj,ptj, Kvjc,
psi, pvj, and Tsj.

5.6 MASS FLOW RATE

5.6.1 Mass Flow Rate at Plane x. The mass flow rate hxat plane x shall be calculated from

h, = &hj),
,=1
= 51
c2 n
2
,=I
( p j q cos *j cos 4j) (5.6-1)

5.6.2 Fan Mass Flow Rate. If f i 1 and f i 2 are both acceptable, see Par. 4.2.3.

(5.6-2)

If only n i 1 or f i 2 is acceptable, lj7F = f i l or ni2 as appropriate. (5.6-3)

If neither f i 1 nor f i 2 is acceptable, r r i F = m 3 . (5.6-4)

5.7 FLOWWEIGHTED AVERAGES

The averageswhich properly represent the mass and energy flows through thefan and reduce to the
gas motion shall be
customary one-dimensional values in the case of uniform,parallel, constant density
calculated as follows [Ref. (IO)].

5.7.1 Average Static Pressure at Plane x

(5.7-1)

c
j=l
n
(Vj cos * j cos 4j)

5.7.2 Average Density at Plane x

c
j=l
( p j y cos *j cos 4j)
C2nh,
-
Px = - (5.7-2)
c n

j=l
(Vjcos t / ~cos
~ 4j) A, cn

j=l
(Vj cos I/J~COS4 )

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ANSI/ASME PTC I1 -1 984

FANS AN AMERICAN NATIONAL STANDARD

5.7.3 Average Temperature at Plane x

2
j=1
(TsjpjyCOS Qj cos C$j) Ax 2
j=1
(TsjpjyCOS f i j COS 4j)
Ts x E -
- (5.7-3)
C,n mx
2j =1
( p j y cos * j cos 4j)

5.7.4 Average Specific Kinetic Energy at Plane x

(5.7-4)

5.7.5 Kinetic Energy Correction Factor at Plane x

(5.7-5)

5.7.6 Average Velocity Pressure at Planle x

PxeKx
Pvx =- (5.7-6)
c
11

5.7.7 Average Total Pressure at Plane x

PIX = Psx + PYX (5.7-7)

5.7.8 Average Absolufe Pressures at Plane x

Prax = Psx -k c13Pb (5.7-8)

Ptax = Ptx -k c13Pb (5.7-9)

5.8 FANINPUT POWER

The fan input powerP, shall be calculated from oneof the followingas appropriate.

5.8.1 AC Motors (Three Phase)

(5.8-1)

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5.8.2 DC Motors (Calibrated)

E'I'qh.1
P, = ~
(5.8-2)
c14

5.8.3 Torque Meters

P - TN
(5.8-3)
"I
5

5.8.4 Steam Turbines. (Refer to PTC 6 or PTC 6s.)

P, = PT (5.8-4)

5.9 FAN SPEED(SLIP METHOD)

When the speed is measured by the slip method, the stroboscope i s operated on linefrequency and
the slip is determined by measuring the period of time a single mark on the shaft 'passes a fixed
reference mark illuminated by the strobe light a set number n of times (e.g., ten times). Fan speed shall
be calculated using

120n
slip = - (5.9-1)
tnP

120 f
synchronous speed = - (5.9-2)
nP

N = (synchronous speed) - (slip) (5.9-3)

5.10 MASS FLOW RATE - SPECIFICENERGY APPROACH

When the mass flow rate - specific energyapproach [Ref. (I)]is selected, the following calculations
shall be performed.

5.10.1 Fan Mass Flow Rate. (Refer to Par. 5.6.2.)

5.10.2Fan Mean Density

Pl + P2 (5.10-1)
Pm =

5.10.3Fan Specific Energy

(5.10-2)

5.10.4Fan Output Power

m F YF
Po = - (5.10-3)
6

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ANSVASME PTC 1 1 -1 984

FANS ANAMERICANNATIONALSTANDARD

5.10.5 Compressibility Coefficient

(5.10-4)

5.10.6Fan Efficiency

PO
r]=- (5.10-5)
Pr

5.10.7 ConversionCalculations for / h F and yF [Ref. (16)]. When operating conditions differ from
specified operating conditions, converted performance shall be calculated using

b=($r(z) (5.10-6)

Kpc = 1 - b(I - K,)

qkc - ( k c - I)(I + + Kpl)
(5.10-7)
qk - (k - 1)(1 + [I + K,])
Plc
Pmc =- (5.10-8)
K,C

(5.10-9)

Y, = Y, (2)2

(5.10-10)

MFcYFc
P,, =- (5.10-11)

P/, = P/ (2)(5)
KPC
(5.10-12)

77,= f (5.10-13)

5.11 VOLUME FLOW RATE - PRESSURE APPROACH

When the volume flowrate - pressure approach [Ref. (I)]i s selected, the followingcalculations
shall be performed.

5.11.1FanCas Density

(5.11-1)

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O 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.0% 0.09

z

FIG. 5.2 COMPRESSIBILITYCOEFFICIENTS (VOLUME FLOW - PRESSURE APPROACH)

(Reprinted fromStandard 51-75 by permissionof the AmericanSociety of Heating, Refrigerating andAir-Conditioning Engineers, Inc.)

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5.11.2 Fan Volume Flow Rate

c2m F
QF=- (5.11-2)
PF

5.11.3 Fan Pressures

Fan total pressure pFL= p12-pli (5.11-3)

P2eK2
Fan velocity pressure pFv= - (5.11-4)
c11

Fan static pressure pFs= pF1- pFv (5.11-5)

5.11.4 Compressibility Coefficient

(5.11-6)

(5.11-7)

zln(1 +x)
K, = [or use Fig. 5.21 (5.11-8)
xln(1 + z )

5.11.5 Fan Output Power

(5.11 -9)

5.11.6 Efficiency

Fan total efficiency r],= PO

-
p/
(5.11-10)

Fan static efficiency qs = r], pF.

P F1
(5.11-11)

5.11.7 Conversion Calculations for QF and pH [Ref. (4)]. When actual operating conditions differ from
the specified operating conditions, converted performance shall be calculated using

(5.11-12)

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a = In(1 + x,) = In(1+ x ) In(1+ z )

(5.11-13)

xC=ea-1 (5.11-14)

(5.11-15)

Kpc = K p / K p / K p c (5.11-16)

(5.11-17)

(5.11-18)

(5.11-19)

PFsc = P F t c - PFvc (5.11-20)

(5.11-21)

PIC -
-P I ("6)
- ( y 3 (z) (5.11-22)

(5.1 1-23)

5.12 UNCERTAINTIES
Systematic U s and us and random U R and uR uncertainties shall be calculated for each of the
performance variables according t o the approach chosen for calculating the results of thetest. The
systematic and random uncertainties for any particular variable can be combined using

+
u2 = (uR12 (us)2 or u2= (uR)'+ ( U S ) * (5.12-1,
5.12-2)

The equations listed below (some of which are derived in Appendix D)shall be applied to both
random and systematicuncertainties by substituting the appropriate individual values. Theindividual
values should reflect the actual circumstances.(Appendix E lists ihdividual values that generally reflect
circumstances that meet Code specifications.)
Paragraphs 5.12.1 through 5.12.11 apply to bothapproaches. Paragraphs 5.12.12through 5.12.16 apply
only tothe mass flow rate - specific energy approach. Paragraphs5.12.17 through 5.12.22 apply only
to the volume flow rate - pressure approach.

50

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 ASME P T C * 3 3 B 9 m 0759b70 0053327 B m

ANSI/ASME PTC 11 -1984

FANS ANAMERICANNATIONALSTANDARD

5.12.1 Mass Flow Rate at Plane x

(5.12-3)

(5.12-4, 5.12-5)

(5.12-6, 5.12-7)

as appropriate. See Par. 5.6.2.

A general equation will beuseful in calculating uncertainties of other results.

U i F = "1'Ui1 + w:uf' + (5.12-8)

where

m F W1 W2 W3

(Ih,+ m#2 1/2 1/2 O

A1 1 O O

4 O 1 O

4 O O 1

5.12.3 Average Static Pressure at Plane x

(5.12-9)

5.12.4 Average Density at Plane x

(5.12-10)

5.12.5 Average Temperature at Plane x

(5.12-11)

51

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 ANSI/ASME PTC 1 1 -1 984
AN AMERICANNATIONALSTANDARD FANS

5.12.6 Average Specific Kinetic Energy at Plane x

tan2GjUij + tan2
+ 4( (5.12-12)
57.302

whtere
'
cos2
eKj= 2 VfCOS2 +j

5.12.7 Average Velocity Pressure at Plane x

(5.12-13)

5.12.8 Average Total Pressure at Plane x

u2 ='I 2(3) 2(
n2 I =1 Ptx
2

UiSj+
I =1
pvjcos2Ptx
*j
2

1
(5.12-14)

5.12.9 Average Absolute Pressure at Plane x

(5.12-15)

5.12.10 Fan Input Power

u2
PI
- 2
- uFsp + u : +
~ U'W for AC motors (5.12-16)

u;/ = uFsp t + u: + u: for DC motors (5.12-17)

u'., = uFsp + u: t u; for torque meters (5.12-18)

u;, = u& + Uit for turbines (5.12-19)

5.12.11Fan Speed

u; = u; for
electronic
counters (5.12-20)

u; = u: + u: for slipmethod (5.12-21)

52

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 ANSI/ASME PTC 11 -1 984
FANS ANAMERICANNATIONALSTANDARD

5.12.12 Fan Mean Density

(5.12-22)

(5.12-23)

5.12.14 Fan Output Power

53

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 ANSVASME PTC 1 1-1 984
AN AMERICANNATIONALSTANDARD FANS

5 - Psl) PS1
W1 m 1 PS1

+[KG
+

Yç (
Pvl PS1

Pl Psa1
P l ( PS2

2 ~ : Psal
PS1

~ r n )I2 u:s1

(5.12-24)

5.12.15Fan Efficiency

u; = uto + u;/ (5.12-25)

5.12.16 Conversions

U i F C= u& + u; + L& (5.12-26)

u;çc= u;ç + 4u; (5.12-27)

UiOC = + su; + u;
Uio (5.12-28)

u& = u;, + su; + u;, (5.12-29)

u',c = u', (5.12-30)

5.12.17FanGas Density

UEF = u;, (5.12-31)

5.12.18 Fan Volume Flow Rate

(5.12-32)

54

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 I

ASME P T C * l L 8 4 W 0757670 0 0 5 3 3 3 3 T m

ANSVASME PTC 11 -1 984

FANS ANAMERICANNATIONALSTANDARD

5.12.19Fan Pressure

(5.12-33)

(5.12-34)

(5.12-35)

(5-12-36)

5.12.21 Efficiency

(5.12-37)

u& = UGI (5.12-38)

5.12.22 Conversions

(5.12-39)

(5.12-40)

u;Fvc= U i F V + 4u; + u;l (5.12-41)

55

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 ASME P T C m 3 3 8 4 W 0757670 0053332 ~ ~~ L W

ANSI/ASME PTC 1 1 -1 984

AN AMERICAN NATIONAL STANDARD FANS

u;Fsc= u;Fs 4u; + + u& (5.12-42)

u;oc = u;* + su; + u;, (5.12-43)

UZplc = u;, + su; + u;l (5.12-44)

u2 = 2 (5.12-45)
‘Itc

56

I -.
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 ASME P T C * L l 8 4 m 0757670 0053333 3 m

ANSI/ASME PTC 11 -1 984

FANS AN AMERICAN NATIONAL STANDARD

SECTION 6 - REPORT O F RESULTS

6.1
GENERAL REQUIREMENTS in charge of thetest, and the representatives of the
various partiesto thetest. It should clearlyidentify:
The results of the test shall be presented in a (a) manufacturer
written report.
(6) type of fan(s)
The preparation ofthe report shall be the respon- (c) serial number(s)
sibility ofthe person in charge of the test who shall (d) owner and location
certify its correctness.
(e) specified fan boundaries
Prior towritingthe report,the parties shall
( f ) specified fan performance
decidewhether to use SI units, U.S. customary
(g) specified operating conditions
units, or both. This selection will generally depend A description of the system of which thefan i s a
upon the units in which the fan performance is
part and any other auxiliary apparatus, the opera-
specified.
tion of which may influence the test result, shall be
included. If any modifications have been made to
the fan or to those parts of the system that would
affect fan performance which are deviations from
6.2
TEST REPORT theoriginal design, they shall bedescribed in
The following subsections shall be included in detail.
the test report. The descriptions of each of the
subsections that follow include the information
6.2.3 Test Procedure. The test procedure shall deal
that shall be contained in thetest report.
with the sequence of events followed during the
(a) Abstract test program. Items such as equipment operating
(b) Introduction conditions for the various tests shall be described.
(c) Test Procedure
For instance, in a system with multiplefans, the test
(d) Instruments and Methods of Measurement procedure may include tests of each fan’s perfor-
(e) Methods of Calculation
mance as well as of all fans operating in unison. The
( f ) Results test procedure must indicate whichfan was operat-
(g) Discussion
ing during each test. Any preliminary exploration
(h) Conclusions required to locate traverse planes shall be de-
( i ) Appendices
scribed here.

6.2.1 Abstract. The abstract i s intended to providea

6.2.4 Instruments and Methods of Measurement.
brief introduction to and summary of the test. It
This portionofthereport shall describewhat
shall state the location and type of fan, the reason instrumentation was used for thetest, where it was
for testing, the specified fan performance, the
located, and how it was calibrated. Details concern-
measured fan performance converted to specified
ing the instrumentationused, including the instru-
operating conditions, and the conclusions drawn
ment’s manufacturer, model number, serial num-
from the test results.
ber, and date of calibration, shall be located in
either this section or, if preferred, in an appendix
6.2.2 Introduction. The introduction shall identify depending uponthe quantity of informationto be
the fan being tested, and list the authorization for included. The location ofeach instrument is usually
the test, the test objective, contractual obligations best identified on a sketch of the fan and duct
and guarantees, stipulated agreements, the person system. If instruments or measurement methods
51

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 ASME P T C * 3 3 84
~ ~~~
m 0759670
~~
0053334 5 M

ANSI/ASME PTC 11 -1984

AN AMERICANNATIONALSTANDARD FANS

other than those specified in this Code are adopted, Graphical presentations such as plotting the test
reasons for such decisions shall be explained in point@) on the specified fan curves maybe helpful
detail. in presenting and interpreting the results.

6.2.5 Methods of Calculation. The techniques used 6.2.7 Discussion. The results and observations ob-
to reduce theraw data to fan performance parJm- tained from the test shall be discussed.Possible
eters shall be documented. A sample calculation sources of errorsin thetest and the uncertainties of
which may be a computer output ora calculation the results shall also be discussed. Actions takenby
sheet shall be presented. This section shall explain the person in charge of the test to remedy incon-
any conversion factors applied to the test measure- sistencies in accordance with Par. 3.10 shall be
ments to compensate fordeviations in the test documented here.
conditions from those specified.
6.2.8 Conclusions. Any conclusions drawn from
the test results shall be simply stated or itemized.
6.2.6 Results. The test resultsshall be presented in a
clear format such as the ResultsSummarySheet
from Appendix A of this Code. This presentation 6.2.9 Appendices. This portion ofthe report should
shall include both the measured fan performance, include any information that will clarify any portion
fan performance converted to specified operating of the test report or make it a complete, self-
conditions, and uncertainties in the performance containeddocument. This can include, without
variables.Sufficient informationaboutuncer- beinglimited to, tabulated data, equipmentor
tainties shall be presented so that both systematic instrumentation illustrations, calibrationapparatus
and random components can be identified. Gen- details, resultsof preliminary inspections and trials,
eral observations concerning thetest environment, computer codes, computer output,and any special
fluctuationsof test conditions,orotherthings calculations such as those to determine theuncer-
relevant to thetest shall be recordedin this section. tainties of the measurements or results.

58

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 ASME P T C 8 1 1 AL( m 0757670 0053335 7

APPENDIX A

TYPICAL RESULTS *SUMMARY

AND DATA SHEETS

59

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 RESULTS S U M M A R Y

From
Date Time: Test No. to

Plant User No. Name/Unit

Mfg. Fan: Function

al No. Curve Contract

SPECIFIED OPERATING CONDITIONS:

Fan Speed N Specific Heat Ratio k
Inlet Gas Temperature t, Gas Being M o v e d
Inlet Static Pressure P,, InletDensity total or static 0
DESIGN FANPERFORMANCE PARAMETERS:
Flow Rate m F or QF 0 Fan Input Power P,
Fan Pressure pFs0 or pFf0
Fan SpecificEnergy y,

INLET CHARACTERISTICS:
Duct Area A, No. Ports No. Points/Port
Probe Type

OUTLET CHARACTERISTICS:
Duct Area A, No. Ports Points/Port
No.
Probe Type

FLOW TRAVERSES AT OTHER THANFANBOUNDARIES:

Identify Location
Duct Area A, No.
Points/Port Ports No.
Probe Type

* RESULTS:
OPERATING CONDITIONS:
Fan Speed N Inlet Gas Temperature t ,
Inlet Static Pressure pI1 Outlet Static Pressure p12
Barometric Pressure po Line Frequency f
Dry Gas Composition by % CO, %O2 % CO
Volume measured at %N2 % %
Inlet 0 or Discharge 0 % % %
Inlet
density total Os toart i c 0 Specific Humidity S
Specific Heat Ratio k

* FANPERFORMANCE PARAMETERS:
Converted to Specified
As Measured
Operating
Conditions
Flow Rate m F or QF
Fan Pressure pFs0or pF,0
Fan Specific Energy yF
Fan Input Power P,
Fan Efficiency 11 0 qf 0 or v, 0
NAMES OF TEST PERSONNEL:

Approved
Date Test Supervisor:

* Identify measurement units

60

" P "

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 ASME PTC*33 8 4 m 0759b70 0 0 5 3 3 3 7 O m

FAN TEST DATA SHEET

TEST DATE TIME to PAGE of

User Name/Unit No.

Identification
Fan: Function No. Barometric Press.

Recorded by Checked by Ambient Temp.

Probe No.

Additional sheets should be prepared for data on speed, input power, ambient conditions, and gas
properties. Sample data sheets appear on the following two pages.

61

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 SAMPLE DATA SHEET
GASANALYSIS A N D AMBIENT CONDITIONS
AMBIENT TEMPERATURE

Date Time: From to Recorded by

Test No. Fan Identification No.

nt User No. Name/Unit

62

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 ASME P T C * l L 84 0759b70 0051339 4

SAMPLE DATA SHEET

POWER
SPEED

I20 X line freq.

(cps) 120 X no.
counts* -
Speed = Synchronous - slip =
no.of motor polesseconds* X no.ofpoles

Pulsefreq.*(cps) -
-
Speed =
60 X no. pulses/rev.
Torque* (ft lb) X rpm -
-
Power =
33,000
f i x volts* X amps* X power factor** X motor eff. X meter calib. coeff.
Power =
745.7
- hP
*Average quantities **Power factor = cos (average phase angle)

Date From Time: to by Recorded

Test No. Fan Identification No.

ant User Namelunit No.

63

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"
Licensed by Information Handling Services
 ASME PTC*LL 8 4 m 0759b70 005L340 O m

APPENQIX B
COMPUTER CODE AND
INPUT FORMS

The following computer code was originally developed under a grant from the Electrical Power
Research Institute and modified by the PTC 11 Committee. This computer code is available i n the
tape form from:
Electric Power Software Center
University Computing Company
1930 Hiline Drive
Dallas, Texas 75207
(214) 655-8883

65

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 OF FAN PERFORMANCE
FOR DETERMINATION
FORM
INPUT
PROGRAM

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
Licensed by Information Handling Services
CARD NOS. 12 thmuah N. See NOTESabove

COPYRIGHT American Society of Mechanical Engineers

0
8
10 I.1 I I I I I I I I I.1 I I I I I I I I I.1 I I I 1 I I I I !.I 1 I j I I /I ) I I\ I I 1 I I
e I I I I I.1 I I I l l 8 ’ 1 I/ ( ‘\(-I
/ I
aI I 1 I I I!!!!!! 0 l l 0 I il
0 I I I I I Id I I I 0 , l 0 I I aIi#l
 ASME PTC*KLL A4 m 0759670 0051343 b m

3
4 T H I S PRCGRAH U I L LC A L C U L A T ET H EP E R F O R M A k C E
5 C OF AUTSFHIAN
El iG METHOD P R E S C R I B E D I h : C
6 C C
7 C A.Sak'eE.
P.TeCe 11 CRAFT CODE SEPTERBER 1 9 8 2 C
.-
P
8
9
10
1
12
13
14
15
16
17 PROGRAHHED
BY:
16
19 DATE :
20 C
21 C UPDATEC
BY:
22 C
23 C DATE:
24 C
25 C UPCATEO
BY:
26 C
27 C DATE :
28 C
29 C*
33 C*
31 C
32 JC REAL t K( K
V TJ C
J (MU
(MC07
(MCOT1
,KDCTZ tHOOT3
33
34 C
1 9 KC * h2 (KRHO ,N VCOTC
35 INTEGER i
36 C
37 CHARACTER * 3 IAtJS
,TERM
tTAG*:7
38 C
39 C
40
41 1
COWMOlv / AVRGS / ,PTX
(RhOX
;F:$ ((P(PPSTVAAXXX
9 ALPHAX
9

42 COK.MON / COkST / R0
43
44
COVMON
COMMON
/
/
CGFiSTl
CNTRL
/ C :$E
?NT
S GC
1 PB VIAIR S I HtAI PSO
Sk '
45 COflMON / CCISTRL / I U
NP ,IPR
46 COMMOFi / DATAI / *PPTS1I yPVI (TI ,YAW I
47 IDPRB PlTCt!
48 'COHMOFi / OATAJ / :PBTSJJ (PVJ r Tt P
SSJAJ 9
49 AREA
PRHOJ (PITCI'J
50 lCOFMON / GAS / C02 902 ,CO ( h2 SS
El C O M M O h / PPFRY / R H( R
OHp
1E0 2K 1 ,EKZ ,POHI ,POU0 9
52 1 POROC( R P K(CR P M I ,KC p T tl R
CH O 1 C 9
S3 PTAIC
SY 'C3PMCh / P R F R M l / ALPHAlVALPHA2
55 COflMOk / 3 U T P E / MlrOTC ( Y F C tPOWIC (KRHCC (ETAC (RHOHC
56 COP.MON / L J F A S S / U H D T F R t U Y (FLRP(IURE T A ( URR H O R R t U P O R 9
57 U M D T F S t U YSFt S
JP( UI SE T( A
USR H C P S t U P O S
58 ' C O V M O h / LVASSC / UYDTCR,UYFCK ~ U k H O C k ~ U P D T C S ~ U Y F C(URHCCS S
59 C O Y M O N / OUTVP / OFC (PFTC
,PFVC
VPFSC ,KPC
(ETASC 9
60 1 E TVAET T A (TECT A S
61 P
COI."CIJ / P9OP / K ,H ( r;Li
62
63 CUHMON / iJPAN / UAR
(URR
VUTSJR(GPVLRtUPSJR
64 1 UYAdR tUPCPR VUETAPR,U'dR ,UER
65 2 UTAUR (UPiiR PUPTR
(UFNR
66 COYMON / LSYS / U( U
A( C
R
STSS( GJ S
PVsU
JSPSJS
67 1 UYAk'S (UPCHS t U E T A PV SU* UEW
SS
68 2 UTAUS(UkS
,LPTS
9clFNS
69 / liYCTlR / UMDTlR,UPSlR gURHOlRtUTS1R (UEKlR
70 1CD!4HoN U P T l ,RU P S A l R
71 COMMON / UhCTilR / UMDTZR,UP52R pURH02RtUTSZR VUEK2R
72 1 U P T 2 tR~ J P S 4 2 2
73 COMMON / U N C T i S / U M D T l S t U P S i S, U E H O l S g U T S 1 S, U E K l S
S
775' 'COMMON / UEtCTZS
U P T '(SU P S P
/ U M D f 2 S ~ U P S 2 ~t U R H 0 2 S v U T S Z S1 U E K Z S

68

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 ASME P T C * l L BLJ rn 0 7 5 9 b 7 0 005l3LJ4 B rn

76 1 (UPSAZS UPTiS
77 COMMON / UNCTJR / UMOT3RgUPS3R ,URHOZR*UTS3R VUEK3R 9UPV3R
Ta 1 pUPSA3R UPT3R
79 COMMON / UNCT3S / U M D T 3 S p U P S 3 rSU R H O 3 S t U T S 3 9SU E K 3 rSU P V 3 S 9
80 1 tUPSA5S UPT3S
a1 COMMON / UNCRT / UMCOT (UPX VURHOX VUTSX pUEKX tUPVX t
82 (UPSAX
1 ,UPSX UPTX
83 COMMON / STDY / UFSMR ( U F S Q R ,UFS.YR rUFSPTR,UFSROR,UFSNR r
84 1 UFSPR
85
86 1
COMYOhr / PLKAVG / MDOTl
(PVl PS3
rMDOT2 gMCOT3
,PV2
;F& t P( S
PZ
,PT2
S1
rPSAl
t
9
87 2 t T S 1 p P S A 3P S A Z pTS2 (PFT ,PFS 9
88 3 PFV
a9 COMMON / UVOPRF! / UQFR :fjFFTR
(UPFVR
tUPFSR ,UETATRpUETASR,
90 URHOFR
91 1C0+4MCti / UVOPRS / UQFS (UPFTS (UPFVSpUPFSS
sUETATStUETASS(
92 1 URHOFS
93 COMtlOk / UVPCR / UGFCR t U P F T C S , U P F S C R , U P F V C R ~ U P I C R tUPOCR 9

:i!
96
1
1
C O M M O f i / UVPCS
UETACR
/ UQFCS , U P F T C S , U P F S C S g U P F V C S 9 U P I C S ,UPOCS
UETACS
r
97
98
99
1ci;
iC1
1ci
103
104
iC5
1'67"
106
129
11G
111
112
113 CALL FTAG ( T A G )
114 CALL F b C S F ( ' B A S C 9 C P ' / / T A G )
115 CALL F A C S F ( * a U S EA L T - : R * , * / / T A G )
116 . OPEN(ZOfFILE='ALT-PRe tTYPE=*APR~TA*,HRECL=lZ2)
117
118
148
M
i1334
25
126
127
123
129
132
111
i1 334
135
136
137
138
139
UPUJS
UPT3S == 0.c
3.C
140

Itf
144
145
146
147
148
149
153
151

69

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 1 5 -*
150
154
155
156
157
158
159
163
161 L
162 IF ( TERM rEQe *YES* 1 CALL INPUT1 ( LtICALC,TD,TU,IH 1
163 IF TERM eEQa 'ND' 1 CALL INPUT ( L,ICALC,TD,TW,IH 1
164
165
166
167
168
169
173
i;$
173
174 Ø
.
175
176
177
178
179
182
1e 1 c
L62 35 CONTINUE
183 C
184 TX = C.C
185 C
106
137
D O 51 I
DO 5b J E- 1;::
168 C
189 TX = TX + T I ( I , J )
193 C
191 53 CONTINUE
192
193
194
195
196
197 C CALCULATA
EVtiRAGG
E AP
SROPERTIEA S T H TE E S PT L P F i E C
198 C S U E R O U T I N E GASPRP C
199
200
201
2c 2
$82 C
225
206 C
207
2 li8
209
E
210
211
212
213
214
215
216
217
218
219
E2 2 P2
22 3
224
225
226
227

70

,
COPYRIGHT American Society of Mechanical Engineers
Licensed by Information Handling Services
 ASME PTC*33 B 4 m 0757b70 0 0 5 3 3 4 6 3 m

228
229
235
231
232
233
2’4
235
236
237
238
239
$$Y
242
L

C
O0 bC I = 1,NP
243 WRTTE(Z~SC20)
244 C
24 5
246 C
DO 6 0 J = 1,hT
247
248
24 9
255
251
$B
254

5ii
258
259
260 6 G COFiTINUE
r
261 b
262 I F ( NOTE .EQ. 1 1 THE&
263 WRITE(Zr515û)
264 END IF
265 ENO ÏF
266 C
$81 L

%S; C
CAVRGES
CALCULATE
AVERAGE
PROPERTY
VALUES
SUBFOUTINE
I N TEST
PLANE
C
C
$321
n

273
274
275
276
277
278
279 L
2aa C SAVE
VALUES OF P E R T I N E N TV A R I A E L E S \ A TF A NI N L E T
28 1 c C
AND C A L C U L A T EU N C E R T A I N T I E S C
282 C SUBROUTINE UNCERT
283
284
285
$ 8 70
%PT1 == MOOT
PSX
i;;
291 EKX
PSA1
P T A ~
RHO
CKl
=
;gj&
PSAX

292 CP 1 = CP
293 TS 1 = TSX
294
295 P
pvlT 1
= PVX
z PTX
296
297
298 Il r C
299
309
301
3 S3

71

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 304 UEKlR = SQRTtUEKX)
305 UP 1 R H (U
3C6 UPVlR ? SERftUß~#~
307 n UPSAlR = SQRT(UPSAX1
3ca
309
31U
311
312
313
314
315
316
317
318
319
32G
321
322
32 3
324 G SAVE
WALUES OF P E R T I N E N T
VARIAELES A T FAN
CUTLET C
325 C AND C A L C U L A T E
UNCERTAINTIES C
326 E SUBROUTINE U K C E R T
327
328
329
330
331
332

3% PT" == PTX
337
338 Psi2 PSAX
ALPHA2 = ALPHAX
3:;
341
c

342 L
34 3 UMDTZR = SQRT(UMD0T)
344 UPSZR = SQRT(UPSX)
345 URHOZR = S C H T (URHGX)
346 UTSZR
UEK2R
=
=
SQRT ( U T S X )
SCRT (UEKX)
347
348 UPVZR
UPT2R
=
=
S Q R T (UPVX)
SCRT(UPTX)
349
35L UPSA2R = S Q R T (UPSAX)
351 C
352 CALL ¡.INCEST 4 21VJ,C(ZI,C(ll)tC(13)t~,RHOM,LtR
353
354
355
356
357
358
359
360
361
E
: 364
n

365
366
$287
369
373
371
372
373
374
375
376
377
378
379

COPYRIGHT American Society of Mechanical Engineers

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 3a o URH03R = SCRT(UKH0X)
381 UTS3R == SCRT(UTSX1
SCRTCLEKX)
382 UEK3R
3a3
384
UPV3P
UPT3R
-f S HT(UPVX)
S8RT(UPTX)
I387
eS2 UPSA3R = SQRT(UPSAX1

388
3a F UMCT 3s
UPSJS
== SQfiT (UMDOT 1
SCRTtLJPSX)
39LI
39 1 URi163s = SGRT(URHOX)
392 UTS3S = SQRT(IITSX)
393 UEK3S SGRT(liEKX1
394 UPV3S = SCRT(UPVX)
395 UPT3S = SQRT(kPTX1
396 UPSA3S SQAT (UPSAX)
397
398
399
400
401
4c.2
4c3
4c4
405
4C6
4c7 u
408 C CALCULATEFANPERFORMANCEUSINGTHE
409 C F A S S F L O iR
r ATE/SPECIFIC ENERGY APPRCACH
415 C AND C A L C U L A T EU N C E R T A I P i T I E S
411 C SUBROUTII\;Z MASNRG
S i l B R O U T I Y E UNCERT
412
413 F
414
415
416
417
41e
419
420
421
422
423
Y24
425
425 L
427 I F ( TERM .EC. 'NO' C A L L OUTM ( M G O T ~ K H O C ~ K R H O ~ E T A1 ~ I U
428 I F ( TERY .CC. 'YES' 1 CALL CUTWl C Ili 9 KRHC 1
429
43u
431
432
4 33
434
435
436
437 C CALCULATE
FAFjPERFORMANCE USING THE C
435 c VOLUME FLOk RATEIPRESSURE APPRCACH C
439 C AND C A L C U L A T EU N C E R T A I N T I E S C
44il C S I I C R O U T i N E VOLPRS C
44 i SUBROL'TINE UNCERT C
442 F C
443
444
445
446
447
448
449
450
tg$
451

4 54
455

13

COPYRIGHT American Society of Mechanical Engineers

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 456 I F ( TERM .ECO * N O * CALL O U T V t CF,RHOF,IU
457 I F ( TERM * E C O * Y E S * 1 CALL O U T V l ( IU
458
459
463
461
462
463
464
465
m
468
46Y
4'ft
472
473 GO TO 1 1 2
474 C
475 123 CLOSEC?5,STATUS=*DELETE*)
476 C
477
4 78 L
Il:!
PRINT *,* ENC OF P T C - 1 1 '
47? C A L LE X I T
48íJ C
481
482
483
484
485
486
487
488
489
49il
491
492
493 .3~F902,F8.5,2F9.5,Fl203,2F9.5,
494 1 F 1 0 0F29 0 2 9 F 9 0 3 j I 7 )
495 5 0 3 1 FORMATïfX,A4~F9.3,F903,F8.31F9~Z,F8.5,2F9~5,F~203,2F9~5,
496 1 F10.Z F 9 0 2 r F 9 0 3 p I 7 * * * I
497 5 0 4 0F O R M A T ( 4 6 X v 2 2 H R E S U L T S A T I N L E TP L A N E )
498 5 0 5 0 F O R F l b T ( 5 6 X 1 2 3 H RtEi L T A T OUTLET P L A N E )
499 5060 FORMAT(56X,47HRE$ULT$ b T A U X I L L I A R Y PLANE (FIMOING FLOW R A T
5c.s 5Clj'D FORMA ( 1 H l )
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5c2 5130 FORMAT(1HirZ(132(1H*)/lX)/6~X,
503 1 i 9 W P E E F O R Y A h C ER E S U L T S / / 2 1 1 X1 3 2 ( 1 H * ) / ) )
5c4 5110 F O R M A T ( A H l t 2 ( 3 e ( l H * ) / l X ) / 6 X , ~ ~ H M A C H NO. GREATER THAh C.4,
505 1 /2(1X,3C(lH*)/)/bX~5HPOI%T,5X,8HK*PV/PSA//)
5c6 51ZU FORMAT(lHG,6X,A4,6X,F6rY)
507 5130 FORMAT(1HO ///lJX,
5CB 1 4 9 H P E S C E N f A G E O F TOTAL POINTS
WITH
EACH NO. OVER 0 . 4 , 1 X t F 6
529 5 1 4 0F O E M A T ( A 3 )
51U
511 c:-
5 1 5 0F O R M A T ( 6 ( / ) , 2 C X , * * k' A R K I N G -
NAY N O T HAVE
CONVERGED')
512 END

ZPRTVLLABSRCoINPUT

74

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ASME P T C * 3 3 BL( m 0 7 5 7 b 7 0 0053350 3 m

A
L
3 L
4 C SUCROUTINE
IRPUT
READS THE INP.UT DATAAhD
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INPUT
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(

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13 INTEGER Z
14 CHARACTER S L O C K 8 3
15
16 COFflOl~/ CONST / RO t JC TGC
17 COHMOk h CGNSTf / C Tcc
18 CCMYON / CNTRL / NP 9 ,PI B
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23
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(TI 9 YAY

23 COPMON / D A T A J / P T J ( P S J ( T,SPJV J ,PSAJ T

24 1 9 P I TAREA
CHJ (RHCJ
25 COMMOK / GAS / C02 102 ,CO 9 N2 ,S
26 COMMON / PRFRM / R H O 1 ,RH02 ,EK1 9€K2 * P O W 1 ,POWO 9
27 1(KC (RPMC ,RPHl POkOC g f ? H O lpCT 1 C
26 2 PTAlC
29 CONMOFi / URAf4 / UAR,UR2 l U T S,JURP V(JURP SrJURP B R
3il 1 ,UETAPRpUCR
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34 ( U2F N S ( U P T S tUhS UiAUS

35 COMMON / STCY / UFSMR TUFSCR
,UFSYR
,UFSPTR,UFSROR*LFSNR 9
36 1 UFSPR
37
3d T
39
40
41
42
43
44
45
46
47
46
49
5"
5i
52
53
54
55
56
G
59 C
L = L + 1
6;1 c~*****~**~48******~*************~**t*4*~*******4****~~****~*~****~*4*c
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64
6~ t T I T LRERE
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64
65 C
66 r
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67
60
69
7 .j.
71
72
73
74
75

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 76
77
78
79
o3
81
82
H3
a4
85
3b
87
86
89
: ?'

@i
94
95
96
97
98
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137
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142
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146
147
14rj
149
153
151

16

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ASME P T C * 1 1 81.I m 0 7 5 9 6 7 0 O951352 7 m

152 oï
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156
157 C
158 G O TG 15
159 C
165 23 READ(5 1 O i C ) T C r T W rS
161 WRITE(?,518G)

176
179
186
181
182
185
1-34
185
186
197
186
189
193
191
192
193
194
195
196
9'8'
i99
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5
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211
21.2
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214
215
216
217
216
219
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224
225
226
227

II

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 228 UPVJR 9 UPVJS
229 UPSJR 8 UPSJS
235 UPSR t UPES
231 UYAg!? UYAWS
2 32 UPCHR 9 UPCHS
233 UETAYR UETAMS
234 UUR uws
235 UER UE S
236 UIR
237 UTAUR W U S
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$ 3 8P8R UPL
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242 UA!? 9 UAS
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244 UTSJR UTSJS
245 UPVJR UPVJS
246 UPSJR UPSJS
247
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257
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i165
266
WRITE ( 2
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,
267
268
$93
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i74
275
276
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$83
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284
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285 R E A D AND r l R I T E T E S T PLPNE D A T A C
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292
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294
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3eo
30 1
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3c 3 E T R A V E R S E PLANE DIFENSIONS

78

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ASME P T C * 1 1 B 4 W 0759b70 0 0 5 1 3 5 4 O

304
305
3 06
3G7
3C8
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311
312

;;i
97"
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319
323
321
322
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324
325
326
327
328
329
333
33ì C
332
333
334
335
336
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338 C
339
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342
343
344
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W
348
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349
35J
351
352 P
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354
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356
357
358
359
363
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362
363
364
365
366 c
367
368
369
370
371 C
372 WRITE(Zî562Cl BLCCK
373 C
374 X1 GIM1 / h l
375 x2 2 x1 / 2.
376
377
378
379

79

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 3eJ
38
;e,
3e3
384
O0 5 3 i
D O 50 J
= 1,NP
1,kT
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c

380
389
399
301
302
393
394
395
396
397
398
399 C
430
4C1 C
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427
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4CY
410
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413
414
415
4 16
417
418 C
419
423 .P

421
4 22
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424 L
425 IPRT = IYRT + 1
426 II = I L + 1
427 C
428 IF ( i 1 .Ea* !UT 1 II = G
429 IF ( II .EC. C 1 I P RI TP R T + 2
43':
431
432
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435
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80

I- " -".

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 4 56 1 3 2 5 FOPFIAT
457 FORMAT
459 FORMAT
459 F39YAT
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462 FOQEIAT
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465
466 TROL P A R A H E T E R S / 4 5 X , 4 ~ ( 1 H - ) / )
467
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81

.
COPYRIGHT American Society of Mechanical Engineers
Licensed by Information Handling Services
 532
533
534
515
536
537
gz
536

54 1
542
54 3
54 4
545
546
547
546
549
552
551
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56 2
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564
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566
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568
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573
574
575
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597
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606
627

82

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 LAZSRC UNCE2T

83

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 i3 L
REAL 1J'DOT 9 MOOT1 9
4 C
5 COMMON / AVRGS / MDCT gPSX
tPTX VPVX VPSAX
pPTAX 9
6 1 TSX VRHOX ,EKX ~ALPHAX
7 COMHON /
/
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13 1
14 COKMON / PRFRM /
15 1
16 2 PTA C
17 COMHON / UKASS / UMDtFR,UYFR tUPIR
(UETAR ,URHOHR,UPOR t
18 U M D T F S t U Y, U FST
PU I SE TgAUSR H O P S t U P O S
19 lCOKMON / UPASSC / UMDTCRtUYFCR ,URHOCR,UHCTCS,UYFCS ,URHOCS
20 / LRAK / UAR (URR
,U3SJA ,UPVJR tUPSJR
tUPBR 9
lCOflMOH UYAWR ,UPCHR ,UETAHR,UWR ,UER "JIR t

i;
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COMMON / USYS
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/ U( U
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R
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,UETAYS,UWS
pUPTR
(UFNR

pUPTS
(UFNS
PUES PUIS
P
P
25 L

26 COMMON / U N C T l R 1 U M G T l R , U P S I,RU R H O l R , U T S l,RU E K I,RU P V l R V

27 1 U P T lP GU P S A l R
28 COMMON / UFiCTiR / UM@T2R,UPSZR ,URHOZRvUTSZR VUEKZR pUPV2R I
29 UPT2R (UPSAZR
30 1C3P#ON / UFiCTlS / U M D T 1 S . U P S l*SU R H O l S * U T S lVSU E K lfSL 'PV1S 9

31 U P q1 - ; U P S A S
32 lCOHMON / IrNCT2S / UMO)ZS,UPS28 ,URHOZStUTSZS (UEKZS tUPV2S 9

33 UPT"C (UPSAZS
34 lCOt!MON / LKCT3R / UMDf3R9UPS3R ,URH03E,dTS3R ,UEK3R (UPV3R 9
UP R t U P S A 3 R
165
37
lCOMIIOK / UNCT3S / UM&f3S,UPS3S
UPT3S 'UPSA3S
,l!RH02S,UTS3S vUEK3S tUpv3s t

38 rCO"ON / UKCRT / UMDGT t U P X VURHOX (UTSX ,UEKX

,UPVX t
39 ,UPSX
,UPSAX
4G lCOr!MoN / STCY / Y F T f i R ?UFSQR tUFSYR rUFSPTRtUFSROR, UFSNR 9

41 / PLNAVG /
42 'COVMON
43 1
44 2
45 3
46 COPMON / UVOPRR I
47 L.

48 COMMON / UVOPRS /
49 1
50 COMMON / UVPCR /
51 1
52 COMHON / UVPCS /
53 1
54
55
56
57
58
59 C
60 c**~****9~4*49~*94d*******s+so$*$******4~**4******~***~*44*4*****4****4~**c C
61 C C
62 C Y A S S F L OR
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APPROACH C
63 C
64 C a 4 ~ * + 4 ~ ~ ~ 9 ~ * ~ ~ 4 4 4 $ ~ 4 4 * ~ ~ ~ ~ * 4 4 * 4 4 ~ ~ ~ ~ 4 * 4 4 4 ~ ~ 4 ~ ~ 4 ~ ~
65 C
66 DATA
RAU/.C174533/
67 c-
68
69
UMDOT
UPSX
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70 UffHOX C.
7 1 UTSX - C.
72
73
74
75 L

84

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 I
76 RUNR = UNR / RPHl
77 RUNS = UhS / R P H l
78 FUPBR 2 UPßR / PB
79
89
RUPGS = UPSs PB
81
82
e3
84
85
86
e7
88
89
90
91
92
93
94
95
96
97
96
99
loci
;!i
104
105
1189 a
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1G8
109 . UEK X
110
lfi
1
.
113 UPVX
114
..
a
115 a
116
H i UPTX
119
123
121
...
122 C
123 1 5 CONTINUE
124 C
125 UYDOT = Ut!DOT + UFSMR**2* + UAR+*2*
126 UPSX
URHOX
== UPSX
UFSROR**2.
N*~z.
+ LJRHOX / N * * 2 .
127
128 == UTSX / N**2.
UEKX / K * * 2 .
129
130
131 8 W i- UPVX / k * 4 2 .
UPTX / N * * 2 .
i%
134 C
135 G O TO 99
i39 C
2 s R U T SU
JSTSJS / TSX
i18
140
C

141 C
142
143
144
145
146 C
i$a7
149
150
151

85

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 i%
154
155
156
157
158
159 UTSX
16'3 b
161 EKJ *2.
162 UEKX
163
164
165 m

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168
a
UPVX
169 b

IR UPTX
11.35
174
175
176 C
177 2 5 C O N T I N LIE
c

if! L
UMOOT = UMOOT
z u sx
+
/
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+ UA S 9 4 2 .
HP
182
8f;hiX
UTSX
= UgtiOX
II U T S X
/
/
N**2.
N4920
le3 UEKX = UEKX / N942.
184 UPVX = UPVX / N**Zo
185 n
UPTX = UPTX / N**Z.
186 L
187
188
AUPSX
UPSAX
=
=
SQRT(UPSX1
( AUPSX**Z.
* + PSX
C13*92. 9 UPBSSSZ. / PSAX**2.
r
189 L
190 GO TO 9 9
191 C
3 0 W1
192
193 W2
u3
-
=
5G.:
194
195 C
G O TO (4C,50,60,7G)9IMASS
$89 C
40 W1 - 1.
tZ8 GO T O 8G
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38
2c2
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G O TO 8 C
203 C
204 6G W1 = üe5
2Q5 'r12 = G.5
206 C
2c7 C
208 G O TO R u
2C.9 C
215 n
73 W3 = l b
211 L
212 8C I F ( I P O k . E C O 1 1 THEh
213 UPfR i UFSPR9*2. + UETAMRe47. + UWR**'
214 UP S - UETAHS**Z. + uus945:
215 n END I F
216 L
217 IF ( I P O W .€G. 2 1 THEN
218 UPIR = U F S P R * 4 2 . + UETAMR#92. + UER492. + ULRlt42.
219 UPIS = UETAMSB42. + UES*42. CIS4SZ.
220 r
END I F
221 L
222 IF ( IPOk' .EQ. 3 1 THEN
223 UPIR = UFSPR**2. + UTAUR**Z. + RUkR**Z.
224 UPIS = UTACS942. + RUNS**Z.
22 5
226
227

86

COPYRIGHT American Society of Mechanical Engineers

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 ASME P T C * L L 8 4 W 0757670 0053362 T W

228
229
23C
231 C
UPIR
LIFSFR**2.
EN8'3 =
+ UPTR*(SL.
UFTS*92 .
2 32 IF ( L I .ECO 4 1 G O T O 9C
233
234
235
236
231
238 L
239
240
24 1
242
24 3
$22
$89
$88
250
C

UMDTFR
UP.DT3R+*2.
251
252
UMDTFS =
UKDT3S**2.
END I F
253 C
254 C
255 C
256
25 7
258
259 C
26íJ UYFR
261
262 ..
b

263
264
265
.. t
t i PB
266 PB /
-
26 7
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b
PSAl
--
PSAl

..
RI402

IJB
272
+
. B
t PVL /
273 C
274 UPOR
275
..
b
276 m
277
278
279
28íl
28 1
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*
...
282 b

O
I 2
285
286 b
287 b
288
.
b
289 o

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b
b

294
295
296
291
298
C
C
.
b

299 C
309 AUROIS
30 1 AUROZS
3 c2 URHGMS
3c3 C

87

COPYRIGHT American Society of Mechanical Engineers

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 304
3c5
3C6
307
30 8
309
31íl
311
312
313
314
315
316

;i
323
321
C
UPOS

322
323
324
325
326
327
32 8
3 9
350
331
332
333
334
335
336
337
338
339
390
34 1
342
34 3
344 UETAR = UPOR + UPIR
UMDTFR + RUNR**2.
34 5
346
C
U#OTCR
UYFCR
Z
= UYFR + 4. *+ URHOlR**2*
RUNR**2.
347
348 UPOCR = UPOR + 9. rP; RL;NRlc*2. + UfiHOlR**Z.
349 C
35;.c
UPICR 3 UP R + 9. 4 RUNR**2. + URHOlR**Z.
35Y. UETACR - UEjAR
125
354
355
356
357
353 C
359 -
c
UPOCS = IJPOS + 9 . * RUNS**2. + URHOlS**Z.
369
361 UPICS
UETACS
== IJPIS
UETAS
+ 9. 4 RUNS4*2. + URHOlS**2.
362 ..
322 L
G O TO 9 9
m
367
368
369_
37u
371
372
373
374
375
376
377
378
379

88

,
, I
"
: -

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ASME P T C * L l 8 4 m 0757b70 00513b4 3 m

386 HOOT 1 Sf R **2

381 * 4

*PB PBM/ O P/O TSPS CT3 /

u2
382
383
384
385
* WM2O O*T AMl
((
1 -
PBR*42
PS
4 nOOT
*
386 2R4*2. + 3 / (
387 )**2* 4 u t u1 4
388 It U P V l R MOO
** *
4
MOO
;i;
389 UPVGR
UPV-R
C
393
AUPTlR
AUPTZR
UPT2R
= UPTlR *4
PT1
PTZ
394 lJPFTR = UFSPTR**2m + ( AUPT2R**2. + AUPTlR**2. 1 / PFT**2.
395 UPVZR**2.
UPFVR
39 6
397
AUPFTR
AUPFVR
== S Q R T ( UPFTR 1
S O R T ( UPFVR
PFT
4 PFV
*
398 UPFSR Z ( AUPFTR**Z. + AUPFVR**Pm / PFS**2a
399 C
40G C
401
4 C2
4c3
404
405
$89
408
4c9
410
411
412
413
414
M
W
4 19 UETATR f UPOR + UPIR
423 UETASR ---
LETATR
421
422
UQFCR
UPFTCR --
UQFR~ +
UPFTR + 4.
RUNR**2
RUNR**Z.*+ URHClR**2.
423
424
UPFVCR
UPFSCR
=
UPFVR + 4 *
UPFSR + 4.
RUKR**2.
RUNR**2.
**
+ URHClR**Zm
+ URHClR**Z.
425 CiPOCR
UPICR
=
UPOR + 9 .
=
UPIR
*
RUNR**2* + URHOlR*ItZ.
+ 9 . 4 RUKR**Z. + URHOlR**Z.
426
427 UETACR UETATR
428
429
43c C
431
432 C
433
434
435
436
**
437
438
439
440 *
i *
44 1
442
443
444
445
446
*
447
44a
$28
451
IS
2s
1
==
U P T f S IPr P T 1
UPT2S 8 P T 2
452 S ( AUPTZS**2* + AUPTlS**Z* 1 / PFT**2.
453 UPFVS = UPV2S**2*
*
454 AUPFTS = S C R T ( LIPFTS 1 PFT
4 55 AUPFVS = S C R T ( UPFVS 4 PFV

89

COPYRIGHT American Society of Mechanical Engineers

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 ASME PTC*KLL 8 4 W 0 7 5 7 b 7 0 00513b5 5 W

475
476 UETATS =
UPOS + UPIS
477 UETASS z U E T A T S
473 UCFCS = üCFS"+ RUNS**:?*
479 UPFTCS =
U P F T S + 4. 4 RUF i S**Z o + URHOlS**2.
480 UPFVCS
UFFSCS
==
U P F V S + 4. 4 R i r N S * S Z m
U P F S S + 4a *
RUNS**Z*
+ URHClS**Z*
+ URHClS*E*
481
482 UPOCS Z UPOS ++9;.* RUNS**2. + URHOlSS*2*
483
484
UP ICs
UETACS
=
UPIS
=
UETATS
*
RUkS*sZ. + URHClS**Zo
485
486 9 9 RETURN
487 EkC

90

COPYRIGHT American Society of Mechanical Engineers

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 ASME PTC*LL 8 4 m 0759670 005L366 7 m

J,

5
4 E SUBROUTINE
GASPRP
DETERMINES
THE
AVERAGE PROP¿RTIES OF
5 C THE
FLUID IF TEE F L U I GC C N S I TS CF OXYGEN NITROGEAI C
6 C CARBON WO.%OXIDE, CAReON C!IGX?DE, AND %ATEA VAPOR C
7
8
9
13
11
12
13
14
15
16 CDM:1ON / GAS / C02 *O2 9CO 1NZ ?S
17 COMMOk / CONST / R0 r JC tGC
18 COKMON / CONSTl/ C r cc
19 C O M M O k / PROP / K ,R 9 MU
20 COMMON / CNTRL / NP 9 NT rIAIR T I ~ A S S, I P O &
21 r. 9 PB
22
23
24
25
26
27
28
29
ji
32
13
34
35
36
37
28
39
95
4 i C CALCULATE V I S C O S I T Y C
42 C r
43
44
cC **a4
45
46
47
48
49
53
51
52
53
54
55
56
57
5a
59
60
61
62
63
64
65
66
67
68
69
79
71
72
73
E
91

COPYRIGHT American Society of Mechanical Engineers

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 &6
87
Rfi
89
9.2
91
92
93
94
95
96
97
98
99
1CíJ
131
122
103
i C 4
i C5
1C6
137
138
1c9
i13
111
112
113

ZPRTeL LAtiSRCoAVPGES

92

COPYRIGHT American Society of Mechanical Engineers

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 ~

ASME P T C * l l 8 4 W 0'257b70 0 0 5 1 3 b 8 O

i
7
5 L L
4 C SUi3RCUTlh'E AVRGES
CALCULATES THE
AVERAGE C
5 C VALUES OF FLOd PARAEETERS I k A TEST
PLAIvE C
6
i
9
l u
11
12 REAL HDOT ,MU ?E.:
13
14
15

li
19
ZÜ
21
22
23
24
25 ,.
26
27
23
29
33 DATA Z / 2i /
31 RATA RAD / .G174533 /
32
33
34
35
36
z7
38 C
39 RV
4J psv
41 V
42 TRV "

43 RV3
44 fi
45 C
46 DO
47 30
413 C
49
5-3
51
52
53
54
55
56
57
Ei3 P
11 CONTINUE
59
63
61
02 CALCULATE
AVERAGE
VALUES C
"
63
64
65
66
67
68
6Y i
72
71
72
73
74
75

93

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COPYRIGHT American Society of Mechanical Engineers "

Licensed by Information Handling Services

 ASME P T C * L L BL( m 0 7 5 7 b 7 0 0053370 7 W

152 6J9EI FORMAT ( 4 3 x 1 *ABSOLUTE S T A T I CP R E S S U R E ' 9 5 X v F 7 . 3 , * KPA*v</)

153 5 1 3 3 FORMAT 4 3 X *AL OLUTE TOTAL P R E S S U R E * , E X 9 F j : f r * I N . UA //J
6130 FORMATI43X:*AB$OLCTE TOTAL PRESSL!RE*96X,F r * KPA*,//!
154
155
156
5 2 0 0 F O ~ ~ A T ( S ( / ) ~ l O X , * O P EI N
5 2 1 0 FDRMAT(1HC 39Xv50(1H*)/4GX 5 0 ( 1 H * ) )
"-
KL E T FAN NO TRAVERSE MADE AT INLET')
157 5 2 2 0 F O R t 4 A T ( 4 ( / f a 2 8 X 1 3 2 H O N L Y M A t S F L O k RATE
'rlILL @E USED*4(/))
158 52311 FORMAT
159 C
16U END

8 P R T f L LABSRCeOUTH

95

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 1
3
4 C SUaROUTIFlE
ObTM
OUTPUTS
ZESULTS F R O M H A S S FLOW RATE / C
5 C S APPROACH
P E C I F I C ENEAGY C
6 C C
7
8
9
i3
11
12 HOGTIKRH
PEAL
13
14 INTEGER Z
15
16 COHMOh / PRFRM / RHO1 * R H 0 2 ,EK1 iEK2 IPOWI T P O ~ O t
a7 1 POWOC 9 R P H l ,PPMC ,KC pRHO1C c T 1 C I
18 2 PTAiC
19 COMMON / PLNAVG / HDOTl tMDOT2
,HDCT? ,PS1 $PS2 9
23 1 I P,VP2VP1S 3 $F1 *PT2 tPSAl 9
21
22
z IcIP9P
TS
FTST
ASA
22l3
PFV s,.-
KP
tPFS t

23 COFMOK / PROP / K- - .R .PU

24 COMMON / OUTHE / MDOTC ;YFC ;PÖWIC ,KRHOC t E T A C ,RHOKC
25 COWMON / UKASS / U M D T F R p U Y,FURP9Il R i E T~AURR H O P R ~ U P O R 9
26 1 U M D T F S I U Y, U
FS (PUI S
ETAS *URHOMSIUPOS
24 C O M M O N / UMASSC / UMDTCRtUYFCR rURHOCE,UNCTCStUYFCS tURHOCS
28 COMMON / I;VPCR / UQFCR
.."." ~ U P F T C R , U P F S C i ? p U P F V C R , U P I C R ,UPOCR
ZY 1 UL 1 A L K
55 C O P M O N 1 UVPCS / UQFCS
.. - - . - - t U P F T C S V U P F S C S , U P F V C S , U P I C S pbPOCS
I
31 A LltTACS
32 COMMON / U R A N / UAR rURR (UTSJR 9iJPVJRtUPSJR
tUPBR
33 1 UYANR SUPCHR *UETAHRIUWR .UER *UIR *
34 1 UTAUQ ;UNR ;UPTR ;UFNR .
35 COMMON / USYS / UAS ,URS I U T SgJUSP V J S IUPSJS "JPBS 9
36 1 UYAUS
pUPCHS
,UETAPStUWS
tUES tUIS t
37 L UTAUS
rUhS
9UPTS
tUFI:S
38
?9 DATA Z / 2 G /
43
41
42
43
44
45
46
u7
4b
49
53
51
52
53 uN = SPRT ( UHGTFR + UFICTFS 1
54 RAR S C A T ( UMDTFR
55 SYS = SQRT ( iJFtCTFS 1
AUN = UA t HDOT
Sb
57
5s
ARAN
ASYS
SYS
= RAK ** HDOT
FOOT
59
69
PCCN
?CRAN
= UR
GAN ** 130.
1LO.
6i n
PCSYS = SYS 3 loc.
5.2 L
65 I F( I lilaEC* 1 THEN
64 W H I T E ( Z p S E B C ) #DOTIAUNIPCUN,ARAN,PCRANIASYS,PCSYS,PCSYS
65 k2ITE (Z,5CGl)
66 ELSE
67 WHITE ( Z 9 6 C G G ) MDOT~AUNtPCUNpARAN,PCRANIASYS,PCSYSpPGSYS
65 #RITE (L95OOl)
EEiD IF
97 c

71
72
UN
RAN == SQRT UYFR + CYFS
SGRT ( UYFR 1
73 SYS 1 SQRT ( UYFS 1
74 AUN [J& 4 YF
75 ARAK = RAN * YF

96

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 76 ASYS = SYS * YF
= R A & *4 ì!kc.
77 PCL'N = uh!
75 PC9AN CO.
79 r
PCSYS = 2 Y S * 1cc.
83 b
si
RL
83
8s
86
67
P6 C
89 SQRT ( UP I R UPIS
9d SkRT UP I R
01 SQRT* ( UPIS
92 UA POXI
3 RAh
SYS
** PCV1
POW1
95
90
97
u4
RAN
SYS
*** 1cc
103
1CC.
ça c
99
lob
121
1c2
1C3
1C4
1c5
1Cb c
137 ur4 = S C R T ( UPOR + UPOS 1
1C1 RAN SGRT ( UPCR
1c9 SYS = S G R T ( UPOS 1
11u
111
Auk
AR4N == Uk
RAN
4 PCUC
* PGkG
112
113
114
115
116 c
117
118
119
1 ¿!ci
121
122
123
124 C
125 UN SQRT t UETAR + UETAS
126 !?AN S4RT ( UETAR
127 SYS = SQRT ( UETAS )
126 AUN
173 ASL:J
1::':
131
i 32
133
134 C
135
136
' 37
1.8
-
P

Ulu S09T ( URHOMR + URHOMS

129 DAN = SQRT ( URHOMR
URHOMS 1
149
141
SYS
AUN =
SZRT
UN * t RHO#
M AKAN
ASYS = RA4
SYS ** RHCF
RHOP
14it
145
146
147 C
14h
149
155
151

97

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 152
153
154
155 L
156
157
:5e
159
16il
161
lb2
163
164
165
166
167
162
i# WRITE ( Z I l O O C
171
172
173
i32
176
177
178
179
180
j3f ASYS SYS r) PLJCTC
L92 PCUN = UN 4 1 0 2 .
183
184
PCRAN
PCSYS
=
=
RAN
SYS ** lL2.
10C.

lii
188
199
190
1Si
192
193
1Q4
195
196
197
19E
199
2011
2c 1
2e2 PCSYS = SYS * 130.
2C3
204 F
I ( ru .EQ. 1 THEN
(PCRAfd PASYS I P C S Y S
W R I T S ( Z t S P I C ) YFC*AUh,PCUN,ARAN
L irlriIT~(Zp5Cll)
207
20ti
zc9
210
Zll
32 1 45
215 AilN == URAN
N 4
* POUlc
POWIC
216 4RAN
217 ASYS = SYS * POCIIC
218 PCL'N = uh' ** l2C.
219 PCRAFI = RAN 130.
22 J PCSYS = SYS 1üo.
221
222
223
224
225
226
227

98

M-

-,
COPYRIGHT American Society of Mechanical Engineers -->
'

Licensed by Information Handling Services

 ASME PTCg3384 W 0 7 5 7 6 7 00 0 5 3 3 7 4 6 m

IF
$38
233
C
Eh0
UN = S O R T ( G P O C H + UPOCS 1
231 RAN = S C R T ( UPOCR 1
23"
230
SYS
AUN
= SQRT ( UPocS 1
UN *POWOC
234 ARAN RAK FOWOC
235
236
ASYS
PCUN =
SYS *PO'UIOC
Uh 4 1 3 0 .
237
238
PCRAN
PCSYS
== RAN
SYS
**
15C.
lac.
239 c
24 3 IF ( I U O Z G O 1 1 THEN
WRITE 241 ( Z , 5 C Z C ) POdOC,AUN,PCUN,ARANpPCFìAN,ASYSfPCSYS
H2ITE 242
24 3 ELSE
244 U R I T E (2,6020) POWOC,AUN,PCUY,ARANtPCRAN,ASYS,PCSYS,PCSYS
24 5 WRITE ( Z 9 5 C Z l )
24 6 €NE I F
247 C
248 UR 2 SQRT UETACR + U E T A C S
( 1
249 DAN SQRT UETACR 1
(
250 SYS = SCtRT UETACS 1
(
251
252
AUN
ARAN == UN
RAN **
ETAC
ETAC
ASYS S Y S 9 €TAC
PCUN
PCRAN
== UN
RAh
*
100.
**
100.
r
PCSYS = SYS 100.
L!
W R I T E (Z,5C4C) E T A C s A U N , P C U N r A R A N , P C R A N , A S Y S ~ P C S Y S
n
WRITE (2,SCYl)
$ 3
262
263
264
$22
267
268
269
270
271
G72
L73 1 5 3 3F O R F ! A T ( 7 ( / 1 1
274 20i30 F O R M A T ( 3 1 X , * P A S $F L O kR A T E / S P E C I F I C ENERGY APPROACH
IU'ITH
AeSOLUT
275 1UENCERTAINTIES ,//!/I
276 . ? í I 1F0 O R M A T ( 4 X *9VAKTITY ,iCXt*UNITS*,b2X,:CGMP~TEC*t9X,*T~~AL*
277 1 , 8 X , ' P E 2 C E N T, 6 X , * R A k 3 0 M( 7 x 9* P E R C E N T, 4 X , * S Y S T E f ! A T I C
278 2*5X.*PERCERT*)
279
283
2911 ~FGR~IAT
ltlX9 *R C
X ,M* V
* ?A7LXU, E
*UNCERT * 8X
* U* ,N E : a f * , 6 X , * S Y S T E
OTAL*,7X,*UN CERT
IC*1
'
251 2012 FOPMAT X,*ChCERT*,Z~X,'UNCE~T*,~ *UNCERT*t//)
I284
t5 "O20 FORMAT
506C FORMAT
C) 2( 32(***)9/))
*$(112( *** 1 e / ) d 2 9 X 1 *PER FOR M A N C E RESULT
CU F TI h L E T DEN
255
286
2
5 m e FORMAT
287 5 2 0 1 FORMAT
206 5 0 1 0 FOPMAT
289 5 0 1 1 FOPMAT
293 5Q2C FORYAT
29 1 5 0 2 1 FORMAT
22823 5030 FORMAT
5 3 3 1 FORMAT
294 5 5 5 0 FORMAT I
295 5 3 5 1 FORMAT
296 5 0 4 0 FORMAT
297 5 3 4 1 FORMAT
298 5 3 5 2 FORMAT
299 5 3 6 3 F0PMA.T
3Gil 5 0 6 1 FOQIYAT
331 6000 FORMAT
3 C2 6 0 1 3 FORMCT
3c3 6L125 FORI.1A T

99

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 I O0

,
"
COPYRIGHT American Society of Mechanical Engineers
Licensed by Information Handling Services
 ASME PTC*KLL 8 4 W 0757670 O053376 T W

1
c
3
4
27
8
9
1Li
11
12
13
14 L
15 C O Y M O t + / PRFRM / R H* R
OH l( E
0r E
2KKl 2 ,POW1
rPOWO t
16 1 POWOC t K P M ,KC
l TRPMC 1RHOlC * T I C r
17 2 PTAlC
16 COPMQN / P R F R K lA/ L P H A 1 , A L P H A Z
19 COMMOR / PLNAVG / H D O T l ,MOOT2 rMDOT3 rYF ,PS1 ,PS2 9
20 tPT1 1 rPV1 PS3 ,'T2 tPSAl t
71 2 PSA; 1PSA3 pTS2 tPFT rPFs I
22 3 ,KP PFV
23 C O P M O N / O U T F E / NDOTC ,YFCVPCiiIC ,KRHOC rETAC 9RHOMC
24 r.
COMMON / PROP / K 1E t MU
25
26
27
28
29 L
38 C CALCULPTE
PERFORMANCE C
31 C C
32
33
34 !?HOM
35
36
37
1
2
YF
- A*L P HG CA 1 1 / *
2.

33
39
POHO
KRWO
MGOT *
YF / C 1 6
RHO1 / R t l O M
4iJ
41
42
43 "
44
45
C
P
CONVERT
PERFORMANCE T O S P E C I F I E DC O N D I T I O N S c
46
117
46 B / R P M l 1* * 2 . 1C
49
SS 1
KRHOC * ( 1.
1 1 *
-
KRH
( 1.
( ETA
+ KRH
51 2 A * K ' 1 K ( 1. +
52 RHOMC KGHOC
53 MíJOTC RHOlC RHO 1 R P W l 4 KRHO / K R R O C
54 YFC RPKC / RPP 1
55
56
POIJ'IC
POMOC
( RPMC / RPP
( RPMC / RPI"
RHOlC / RHOl *
KRHO / KRHOC
R H O l C / R H O l 4 KRHO / KRHOC
57 E T P:C
56
59 RETURN
oil C
6: EliE

a'PRT+LLASSRCsVOLPRS

101

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 ASME P T C * 1 1 8 4 W 0757b70 0051377 1 M

14 PIAlC
15
1
COMMON / PLNAVG / MOOT1
tPVl PS3
pMDOT2 fMDOT3(YF
tFW2 ,PT!
,PS1
lPSA1 ,PT2
,PS2 ,
16 9
17 2 9P
,r~Pg
PSTF
TF
SA
SSTAE
L13 v
1s 3 pcu .UD
.R"'
I .

19 COYMON / PROP / K a MU
COI-"OFi / OUTVP / ;PFTC
EFC ;PFWC ,PFSC
,KPC ,ETASC 9
ETAT ,ETATC ,FTAS
1 7
'CONMOK / OUTPE / YDOTC ,YFC ,
OkIC ,KRHOC ,€TAC ,RHOMC

ETAT
13Y1/
ETAS
ZC
7 RPiC
/ ( K - K t - 1. 1 /
RHOF
' l/ PTAlC
K C 9 P7A *
L4 C 1 /
A A L O G ( l! H
1.o l $
-
b.LOG( 1. + Z ) *

* -
I K - I* / KC 1* I
xc z fXP( A 1 1.
KPKPC = Z / ZC xc / K -
1. ) * ( K C - 1. 1 / K C
si KPC =
=
K P / K PKPC
Q F * R FHC / R P M 1 9 KPKP C
59 QFC
PFTC
PFVC
=
z
P F T 4 H H O l C / RHOF
PFV *-
( RPMC / R P P l I * * 2
*
( RPMC /
¡ìHO * KPKPC
PFSC PFTC PFVC
POWIC = P O Y I 9 R H O l C / RHOF **
( RPMC / KPKPC **
POGiOC
ETATC
=
=
PCWC
ETAT
*R H O l C / RHCF ( RPMC / KPKPC

46
ti7 C
ETASC = ETAT *PFSC / PFTC
68 RETURN
69 C
73 EKE

3PRT.L
LABSRCaOUTV

102

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 ASME PTC*ll 8 4 m 0 7 5 9 6 7 0 00511378 3 m

3
4
5
6
7
8
9
13 SUSROUTIh'E
OUTV ( QF,
RHOF, IU
11
12 C O M M O K / PRFRM / RHO: ,RHOZ ,EK1 t tEPKO2W I *POWO 9
13 1 PObOC
,RPH1
(RPHC ,KC rRhO1C qT1C 9
14 2 PTAlC
15 COMMON / P L h A V G
16 1
17 2
18 3
19 COFNOk / PROP 1 MU
2G C O H M O h / CUTVP / QFC tPFTC t P tFPVFCS C PKPC tETASC 9
21 1 E TrAETT b ,TECT A S
22 COHMON / CUTME / KDOTC ,YFL (POLIIC 9KRHCCPETAC (RHOKC
23 C O Y M O K / UVOPRF? 9UPFTR vUPFVR (UPFSR ,UETATR,UETASR,
24 1 !#%FR ..
25 COMMON / UVOPRS 1 ÜGFS VUPFTS
,UPFVS
tUPFSS
,UET.ATS,UETASS,
26
27
1
COMMON / UPASS /
-
I-....-.
IRCIIIFS
UMCTFR,UYFR ,UPIH
9UETAR ,URHOPHIUPOR P
28 1 U M D T F S v U YVFUSP
9UI SE T A S *URHOHS,GPOS
29 C O K N O h / UVPCR / UQFCR a"
,lJPF?CRrUPFSCR,UPFVCR,UPICR ,UPOCR 9
Zr; .I".
U ì I ALK
31 lCOMls,OEj / UVPCS / UUFCS , U P F T C S ~ U P F S C S , U P F V C S , U P I C S ,UPOCS
B
34
1
REAL HP
UETACS
tkC (MCOT1
1KPC
,%DOT2
35
36 INTEGER Z
37
36 GATA Z/ZO/
39
43
41
42
43
44
45
116
r7
48
49
50
51 L
52
53
2
56 ARAiJ = PAN # GF
57 ASYS = SYS *CF
5b
59
PCUfJ
PCRAN == CN
RAF!.
0 iiic.
lZ;.C*
63 PCSYS = S Y S 4 lüG.
61
62
03
04
65
66
67
68
69
73 UN SURT ( ljPFTR + UPFTS 1
71 RAY = SQRT ( UPFTK )
72 SYS = SCRT ( UPFTS
73
74
75
AUN
ARbFJ
ASYS
=
=
UiJ
RAN
SYS 4
** PFT
PFT
PFT

I
103

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 76 PCUN = Uk * 1cc.
77
78
79 C
80 IF( ZU .EO. 1 THEN
81 WRITE (Z,501G) P F T * A U N * P C U N , A R A N , P C R A N , A S Y S , P C S Y S
82 WRITE (2,5Cll)
83 ELSE
54 YRITE (Z‘bClG) P F T t A U N , P C U N , A R A N , P C R A N , A S Y S , P C S Y S
85 WRITE (2,5011)
86 EN@ IF
87 C
88 UN SQRT ( UPFSR UPFSS 1
89 FAN SQRT ( UPFSR
93 SYS SQRT ( UPFSS
92 AUN U h 9 PFS
92 ARAN RAN 9 P F S
93 ASY S SYS 9 P F S
99 PCUN UN 9 100.
95 PCR AN
96 PCS YS
97 C
98
99 ,PCUN,ARAN,PCRAN,ASYSgPCSYS
1GU
101
vPCUN,ARAN,PCRAN,ASYSpPCSYS
H3
104
1c5 C
106
107
10s
li19
110
111
A.S.Y.S ~ s.ys * PFV
112 PCUN = UN * ~UOI
13Ca
113
114
PCRAN
PCSYS
E- SAN
$YS
9
* Ibo.
115
i!$
i:;
120
121
122
123
124 UW
125 RAN
126 SYS
127 AilN
128 LrRAF!
129 ASYS
13ii PCUN
W PCQAN
RAN
PCSYS = SYS
** 1co.
1GC.
133 C
IF ( I U .€C. 1 1 THEN
G
i136 WRITE
WRITE
(Z,50501 P O W I , A U N , P C U N , A R A N , P C R A N , A S Y S , P C S Y S
(Z15G51)
137 ELSE
138 WRITE (2,6050) P O U I , A U N t P C U N , A R A N , P C R A N , A S Y S , P C S Y S
139 WRITE (2,5C51)
140 Eli0 I F
141 C
142 UN =
SQR UPOR + tipos 1
143 RAN SQR UPOR 1
144 SYS =
SQR UPOS 1
145 AUN =
ubi
= RAN
cg0
ok’c
146 ARAN
147 ASYS z SYS ow0
148 PcuN =
UN eo.
149 PCRA N = RAN oc.
153 PCSY S =
SYS GO.
151 C

104

. ..
3
COPYRIGHT American Society of Mechanical Engineers
Licensed by Information Handling Services
 ASME PTC*LL 84 m 0 7 5 7 b 7 0 0051380 L W

152 I F ( X U * E a . I 1 THEN
153 ?RITE (Z,5G601 POUO,AUNtPCUN,ARAN,PCRAN,ASYSvPCSYS
154 l v R I T E (ZtSC61)
15 5 Cl cc
156
157
158 END I F
159
16C UN z SQRT t UETATR + U E T A T S )
lEl
162
RAN
SYS
=
SQST ( UETATR 1
= SQRT ( U E T A T S )
163
164
AUN
ARAN
= UN ETAT
= RAN E T A T .
**
i65 ASYS = S Y S 4 ETAT
166
107
PCUN UH
PCRAhi Z RAN
13C.
1OC. **
16%
169
PCSYS =
SYS reo. *
17t URITE ( Z v 5 C 7 G 1 ¿TAT,AUN~PCUt4,ARANtPCEANpASYS,PCSYS
171 CIRITE (Z15G71)
172
173 1
174
175
176
177
178
179
180
181
182
183
TE4
185
186
i87
UH
RAN == SQRT
SQRT
(
(
URHOFR + UHHOFS )
URHOFR 1
SYS SQRT ( URHOFS 1

*4*
188
le9 Auk = UEi RHOF
193 ARAN = RAhr RHOF
191 ASYS = SYS RHOF
192
193
194
PCUN
PtPAt:
PCSYS
==
=
UN
RAN
SY5
*** lCCe
l0C1
1CO.
195
i 96 I F ( I U .€G. 1 ) THEFI
197 WRITE (Z95C9G) R H O F t A U N ~ P C U N v A R A N ~ P C R A R ~ A S Y S t P C S Y S
CI c r
198
199
2co
201
222
20 3
204
2C5
2C6
zc7
208
209
210
211
212
213
214
215
216
217
218
219
223
221
222
223
224
225
226
227

I05

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 228
229
230
231
232 IF ( I U .ECO 1 1 THEN
233 W R I T E (Z,5&02) Q F C , A U N , P C U N , A R A N , P C R A N , A S Y S , P C S Y S
234 MRITE ( 2 9 5 C C l )
235 ELSE
236 W R I T E (2*6CcIC) Q F C , A U N t P C U N t A R A k , P C R A N , A S Y S , P C S Y S
237 W R I T E (Z15Ci31)
2 36 END I F
239
240 UN SORT ( UPFTCR UPFTCS
24 1 RAN SQRT ( UPFTCR
242 SYS SQRT ( UPFTCS
243 AUK UN *PFTC
A,RAN RAbi 9 P F T C
244
245 ASYS
PCUN
SYS
ulu
*
0
PFTC
130.
246
247 PCRAN RAN * 1631
248
249
PCSYS SYS * 10G.
250 IF ( I U IEQ. 1 ) THEE
251 WRITE (Z,5C12) P F T C , A U N , P C U N , A R A N , P C R A R , A S Y S , P C S Y S
252 W R I T E (2,5011)
r) e r
253 CL3L
254 WRITE (Zl6OlC) P F T C , A U N , P C U N , A R A N , F C R A N , A S Y S , P C S Y S
WR T E ( Z , 5 c l l l )
%Z
257
END 4F
258 Ur4 = S Q R T ( UPFSCR + UPFTCS
259 RAN = SCiRT ( UPFSCR 1
260 SYS == SCRT t UPFSCS 1
UN 4 PFSC
26 1 AUN
RAN 9 PFSC
262
263
ARAN
ASYS =
=
SYS
UN
*
**
PFSC
1001
264 PCUN
265 PCRAN = PAN 1bO.
266 PCSYS = S Y S 4 1û5.
$6687 IF ( I U . E G O 1 1 THEN
262 U R I T E (Z,50 1 PFSC,AUNgPCUNtARAN,PCRANtASYS,PCSYS
27u WRITE (Z,5Q$?)
ri cc
271 LLJL
272 WRITE (Z,6C2G) P F S C , A U N t P C U N t A R A N , P C R A N , A S Y S , P C S Y S
273 # R I T E (Z,SC21)
274 EN5 I F
275
276 UN I: SQRT ( UPFVCR + UPFTCS 1
277 RAI4 = SQRT ( UPFVCF )
276 SYS = SQRT ( UPFVCS
279 N
!!!!. . . . . .. == Uk
RA&
4 PFVC
*
PFVC
ASYS
PCUFi
= SYS *
PFVC
UN 4 1C01
z83
L84
PCRAN
PCSYS
=
= RAN
SYS **
120.
100.
ZR5
286
287
288
289
290
291
292
29 3
294
295 ur1
AUtv
= SQRT 1 U P I C R + U P I C S )
UK d FOWIC
296
QAX I: SGFiT ( U P I C R 1
297
298 ARAN = RAN *
POWIC
299
300
3C1 SYS = SQRT ( i J P I C S 1
*
302 ASYS = SYS POWIC
303 PCSYS = SYS 4 130.

106

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 I
334 c
3f2
307
3CB
3c-9
2fP
312
313 UN = S Q R T ( UPOCR + UPGCS
314 RAN S Q R T ( UPOCR 1
u:
317
SYS
Auk
ARAN
==
=
SQRT ( UPOCS 1
Ut4 POYOC
RAN 9 P O k O C
315 ASYS SYS
**
POUOC

:si
319 PCUN Uh: 130.
PCRAN
PCSYS
=
=
RAN
SYS
**120.
1CC.
323 IF ( IL! . E Q . i 1 THEN
324 WRITE (Z95C60) P O W O C , A U N , P C U N , A R A N , P C R A N , A S Y S , P C S Y S
325 r
kRITE
1 cc
(2,5561)
326 LLJL
32 7 GiRITF (2,6060) P O k O C , A U N V P C U N , b R A N , P C R A N , A S Y S , P C S Y S
325 C i R f T (EL t 5 G 6 1 )

E
332
n
1.
EMD I F
UN
RAN =
SQRT
SURT
(
(
UETACR + UETACS 1
UETACH 1
3% 2;: = SQRT
UN * ( UETACS )
ETATC
232
337
ARAN
CSYS
PCUFl
==
=
PAh
SYS **
U h 4 130.
ETATC
ETATC
338
339
PCRAN
PCSYS =
f RAN
SYS
**
152.
1I;c.
340
341
342
343
344
345
346
34 7
348
34?
353
351
35.2
353
354
355
356
357
356
359
566f
362
OLUTE UNC

382
365
366
367
368

;it"
369

82
375
376
377
378
379
I
107

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 "

I08

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 APPENDIX C

SAMPLE COMPUTER OUTPUT

The following sample output is based on a four-point traverse. Obviously, no real test wil! have as
few pointsas this, but additional pointsare not necessary to illustrate thecalculations andthe results.
Input data and intermediatecalculations, as well as final results, are given. Both actual and
converted
results are shown. The results are given for both the mass flow rate - specific energy approach and
the volume flowrate - pressure approach. The same measurements were used tc obtain theresults
for the two differentapproaches.
D

I o9

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ~~ ~

ASME PTC*lL 8L1 m 0757670 0053385 O

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a
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.. .. .. . .
o,

... ... ... ... ....

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4*

110

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 . .. .
+ N - 4
u 0 H M
0 0 o13

I+
*+ *+
it*
+ +*
+
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*

.+
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O

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 ASME P T C * l L 8 4 m 0757b70 0051387 4 W

** ** *+
**
** ** **
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z
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112

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services F
 *c
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**

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 TOTAL STATiC VELCCXTY PITCH PROBE PROBE
POINT ;&mg: m:ss,“m; ;;;y;; lEHP$TUkE YAY ;p,“t”; pplt;E ID
l (DEG)
----------------- ,,,,,,,,,,,,,,1,,,,-------,---L,,,,,, ,,,,,,,,,,,,,--,,,--,,,,,,,,,,,,-,,,-’,,--------------------------~-----

l.GZ
A! $:*;$i -is:!
L . c ik2;! .91 e we :3% :W s

Bl ;t:;g .56 77. .Q -24.

2 %z! . .95 8 77. E Li 4- f -:8% AXif 3

Licensed by Information Handling Services

1

COPYRIGHT American Society of Mechanical Engineers

GESULTS AT CUTLET PLAKE

POINT PT(J1 PStJ) P!!(J) Rl’OfJJ - EP 1 + ET PROBE RE KVJC KTJ YAU ItER
(IN. UC1 ‘:A:’ (LBP/CU d %F’ (IlEG) WF

2 21.536
21.781 2;.5C4
2L.7.37 1.C43
.932 535.88
53!+91 :E 7654
7657 :X8% kEii'c4S f

"4 21.622
21.174 Zia.bW
23.583 232 E:'3 . :E% .9995c
.99919 l.GOCSS
l.CGC34 263(38.5[32
33417.146 l.GO843
l.CS662 1996
I1. .g 1991 g8';:g; -2;:;: -g:;gp’ f
 ASME PTC*II 8 4 m 0 7 5 7 6 7 0 0053370 4 m

**********************~********~******************
~***********8$**********$$***~***~**~***~*4*******
AVERAGE VALLES AT OUTLET PLANE
"""""""~"""""~"""~""~

FASS FLOU
RATE 186.59 LBMIS

STATICPRESSLRE 20.652 IN. Ut

V E L O C I T YP R E S S U R E e774 IR. kG

TOTAL PRESSURE 21r426 I N . U t

TE6PERATURE 536.17 R

DCNSITY r07651 LBH/CU F 1

S P E C I F I CK I N E T I CE t i E R G Y 52055 FT*LB/LBtl

K I N E T I C EkERCY CORR F A C T O R 1 e039Gt

A a S O L U T ES T A T I CP R E S S U R E 4230273 I h e U A

ABSOLUTE TCTPL PRESSCRE 424mC47 I & . UA

..................................................
**************************************4***********

COPYRIGHT American Society of Mechanical Engineers

Licensed by Information Handling Services
 PERFORMANCE RESULTS
+*******4**4************~~****++++*****************4v*v*************4***********************************4*v**************
******************+4***++*****4*4**444*4*4*4***4*4*********4*******4*8*4*********************4*4*********************************

Licensed by Information Handling Services

rASS FLOh RATE / SPECIFIC ENERGY APPROACH YITH AESOLUTE UNCERTAINTIES

COPYRIGHT American Society of Mechanical Engineers

QUANTITY UNITS C~O;;W;ED TOTAL PERCENT RANDOtt PERCEkT
IiNCERT UNCERT
LKat BkEE:! I
L&M/S lC6.59 1.895 1.778 I.583 1.485 .978 0
“A;%TgLO” 1.043 4
Lrl
5
FT*LB/LBr 1482.67 18.116 1.222 15.647 1.069 a.779 .592 a-
4
0
FAN INPUT HP 344.oc 5.441 1.582 4.199 1.221 3.460 1.006
POYER 0
0
FAN OUTPUT HP 287.34 6.469 2,251 5.478 lc9C6 3.440 1.197
POUER
z
W
D
FAi XTCT .a353 .C23 2.751 .019 2.264 .013 1.564 t-l
EFFICIENCY
o-
LBHICU FT .E7499 .CCC .335 .aco .220 ,000 ,253
I
NONE .97974

c
 FEAFCRWANCE RESULTS COhVERTED TO 915. RPfl AND .07Soc ~Bwcu FT INLET OENSITY
+*+v*******************~~*~*****~*****~*vv*~****v*#**~~***v*********v~********~**~*********************************************
******t*******t**********t*+*****************~*~*****~***~*~*~*********~*****~~**~***~v************************&********************

Licensed by Information Handling Services

PASS FLOU RATE / SPECIFIC ENERGY APPROACH YITH A@SOLUTE UkCERTAINTIES

COPYRIGHT American Society of Mechanical Engineers

QUANTITY UNITS TOTAl F$;$T RAhOOP
LECERT UNCERT
UNCERT

WA’ffTgLQY mm 107.11 1.999 1.867 1.626 1.518 1.163 l-086

FT*LB/LBM’ 1460.24 18.121 1.241 35.60s 1.C69 9.208 -631

HP 340.45 5.816 1.7C8 4.293 1.261 3.923 1.152

HP 284.38 6.66C 2.342 5.496 1.933 3.761 1.323

FAN PER 08353 .023 2.751 .cl.9 2.264 .013 1.564

EFFICIENCY UNIT

NONE .98774

COMPRESS. NONE .99190

COE. RATIO
 VOLUHE FLCW RATE / PRESSURE APPROACH YITH ABSOLUTE UNCERTLINTIES

Licensed by Information Handling Services

PUANTITY UNiTS WW,“” TOTAL SYSTEMAT IC PERCENT
UNCERT P%F:NLT Kix:! K%SST UNCERT sY~N'~m;;Ic
UNCERT UNCERT

COPYRIGHT American Society of Mechanical Engineers

VCLUHE CU FT/h!IN 87C48. 1639.2 1.ea3 1335.7 1.534 950*2 1.092
FLOY RATE

FAN TOTAL IN tit 21.43 .25% 1.2c4 .231 1.080 .114 .533
PRESSURE

FAN STATIC IN YG 20.b5 .259 1.253 .232 1.123 .115 0555

PRESSURE

FAN VELOCI TY IN YG .77 .p1a 2.363 .014 1.049 .Oll 1.471

PRESSURE

FAN INPUT HP 344.cc 5.441 1.582 4.199 1.221 3.460 1.006

POdER

FAN OUTPUT HP 268.52 6.604 2.289 5.528 1.916 3.613 1.252

POVER

FAN TOTAL PER .a367 .C2334 2.782 .019 2.272 .013 1.606
EFFICIENCY UNIT

FAN STATIC PER .aca4 .CZi49 2.762 .018 2.272 .Ol3 l-606
EFFICIEHCY UNIT

FAN OENSITY LBH/CU FT .:-I347 .oot41 -557 .OOC .316 .OciO -459

COMPRESS. NONE .98294

COEO
 *+******************************+***************************************~*
************************+*+*******************************************************************************************************
FERFORMANCE RESULTS CONVERTED TO 5lf. RFM AND .C75t0 LSWCU FT INLET DENSITY
************+**+*********+*++********************************************************‘**********************************************
********f************L**+Ltt.****t*************+*******************************************************************************

VOLUnE FLOY RATE / PRESSURE APPROACH YITH ABSCLUTE UNCERTAINTIES

Licensed by Information Handling Services

QUANTITY UNITS TOTAL sY.5~~5;~‘” PERCENT
CKk2Eo IJNCERT w:LNT i%% i%Ell’ sY;;~m;;xc
UNCERT UNCERT

COPYRIGHT American Society of Mechanical Engineers

CU FT/MIN 86376. 1629.2 1.886

fAN TOTAL
PRESSURE IN Vt 21.54 .i90 1.345 .242 1.126 .158 -736

FAN STATIC
PRESSURE IN YG 20.76 .20b 1.379 .242 1.167 1.992 9.597

FAN VELOCITY
PRESSURE IN YG .7a .016 2.015 .a15 1.876 .U12 1.556

FAN INPUT
POUER HP 343.1a 5.862 1.7cia 4.327 1.261 3.955 1.152

FAN OUTPUT
POYER HP 207.83 6.845 2.378 5.59c 1.942 3.951 1.373

FAN TOTAL
EFFICIENCY PER
UNIT .83a7 .a2334 2.782 .a19 2.272 .013 l-606

FIN STATIC PER .eca4 .E2334 2.782 .019 2.272 .013 1.606
EFFICIENCY UNIT

.
%PRESS* NONE .98367

COHPRESS. NONE .99987

COE. RATIO

*********+********************+*+*+*~*************************************************************************************
*********************+*+*+*********************************************************************************************************
 APPENDIX D
DERIVATIONS O F UNCERTAINTYEQUATIONS

This Appendix deals with thepropagation of uncertaintiesinto the results. Included are derivations
uncertainty equations thatappear in Par, 5.12. The other equations in Par. 5.12 can be
for four of the
derived in a manner similar to one of the fourexamples. All of the derivations follow the approach
suggested in Ref. (2).

DI UNCERTAINTY IN hx,THE MASS FLOW RATEAT PLANE x

The equation for f i x is given in Section 5 as

Ax
m,=--
Cz n
’2 (PjVj cos *j cos 4j)x (5.6-1)

Not all of the variables in this equation are direct test measuremlent.s. We can get closer to
measurements by substituting for pi and 4.

(5.4-5)

vj = C I 2 f E (5.5-1)

We can alsoimprove this analysis by adding two factors, F , and FsmJ to the originalequation. Boththe
number of pointsfactorF, and the steadiness factor F, are assumedequal to unity; therefore, theywill
not change the original equation.However, theywill provide a basis for evaluating the uncertainties
due to number ofpoints and unsteadiness.Substituting for pi and Vi and adding F, and FSm gives

(D.1-I]
c2 n j=7

It willbe helpful to introduceAi which is equal to A,/n and substitute

(D.l-2)

Ai as hi,
Defining the flow through
121

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 (D.l-3) o
The constants C1l,C12, and C2 can be considered exact and, therefore, ignored in the uncertainty
analysis. It follows that

(D.l-4)

Differentiating

j=l

(D.1-5)
o
j=1 j=l

Klineand McClintock[Ref. (2)] recommended asecond power equation

for combininguncertainties.

(;: + (F
(dfi,)2 = - dF, ) 2 sm dF,, ) 2 + ( & d s f i ) 2 + F oerms
- (D.l-6)

j=1

Assuming complete independence of the individual terms, the cross product terms are all zero,
Similarly,

C rhj=m,+fi2+..*+m,
i=l

d c n

j=1
mi = dml + dfi2 + * + dm,

(d 2 mi)
j=1
2
= (dhl)2 + ( d r ~ j+~. ) ~. + + a a + p r d u c t term!’ (D.1-7)
O
I22

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 ASME P T C m l l 84 W 0759670 005L.377 7 W

Hence,

(D.l-8)

Dividing by (h,)*,

2 (dmj)2

( 2)2 ( j=l

=( F, + + (D.1-9)

(2
j =1 m j ) *

I n the manner of Kline and McClintock [Ref. (2)], let

etc., where U i s the absolute uncertainty and u is the relative or per unit uncertainty insubscripted
the
quantity. It is also useful to denote the partial
derivative of a result with respect to a particular variable
as the sensitivity factor 8. For example,

etc.
To develop a compact notation, let
amj
e.!,I. = - for variables in m j
avi, j

I23

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 ah, -
= -- -tan d j m j
a@j

All of these sensitivity factors havethe general form

m j
,g. . = -where g ( v i , j )is a function of vi,j
191
S(Vi,j)

We can also let

j=l
2
j=l
( d f i j ) 2= 2 (D.1-IO)

However,

(D.1-II)

where Ui is the uncertainty in the variable i, and where i = Aj, psi, pb, etc. It follows that

(D.1-12)

Also that

(D.1-13)

Rearranging the equation for m x (D.1-4) gives

Also

+q2)2+(?)2+(2)2]
4

tan2 # j ~ $ j +
+ ( c19
(D.1-14) @
124

.
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 ASME P T C * 1 1 84 M 0 7 5 7 b 7 00 0 5 1 3 7 7 O W

Therefore, by substituting in (D.1-9)

Setting F, and Fsm equal to unity, rearranging, and substituting relative uncertainties wherepossible,

(D.1-16)

This i s Eq. (5.12-3).

D2 UNCERTAINTY IN psx, THE AVERAGE STATIC PRESSURE AT PLANE x

The equation for psxis given in Section 5 as

(5.7-1)

The Vi cos cos terms inboththenumerator and denominator are weighting factors inthe
averaging process. Wewill assume that the contributionsof these weighting factors to uncertainty are
negligible and approximateEq. (5.7-1) by

(D.2-1)

only for the purpose of uncertainty evaluation.

Differentiating

(D.2-2)

Noting that

j=l j=l

125

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 A S M EP T C m 1 1 8 4 W 0 7 5 7 6 7 0 0051400 3 W

and that

if we assume the cross product terms to be zero (because of independence), we find

(D.2-3)

Dividing by p&

(D.2-4)

Multiplying by p$/p$

(D.2-5)
e
Since dpsj/psj= LIpsj, the final equation is

(D.2-6)

This is Eq. (5.12-9).

C93 UNCERTAINTY IN P, FOR A CALIBRATED A C M O T O R

The equation for P, is given in Section 5 as
(5.8-1)

Differentiating

1 o3
dP/ = (WdqM + VMdW) - (D.3-1)
c14
Substituting forW and qM

(D.3-2) e
126

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 ASME PTC*KLL BL( W 0757670 005l1~015 W

Dividing by P,, squaring, and setting cross product terms to zero

( y [( = y 2 + ( ! y 2 ]
(D.3-3)

In terms of relative uncertainties, the result including theeffect of unsteadiness is

u;, = UisP u;M + +uh (D.3-4)

This is Eq. (5.12-16).

D 4 UNCERTAINTY IN pm, THE FAN MEAN DENSITY

The equation for pm is given in Section 5 as

Pl + P2 (5.10-1)
Pm

Differentiating

1
dpm = 7 ( d ~+l dpd (D.4-1) .

Squaring and dropping cross product terms

(D.4-2)

(D.4-3)

This is Eq. (5.12-22).

I27

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 ASME PTC*LL84 m 0759b70 0053403 9
~~ m

APPENDIX E

ASSIGNING VALUES T O PRIMARY UNCERTAINTIES

The equations in Par. 5.12 give the uncertainties of the various results of the test in terms of the
uncertainties in the test measurements and in certain other factors. These measurement and factor
uncertainties, herein calledprimary uncertainties, should reflect the circumstances of thetest. Some
of the circumstances that affect the primary uncertainties are discussed in this Appendix. Typical
values of the primary uncertaintiesare also suggested here. Values are given for both thesystematic
and the random components of the uncertainties where appropriate.

E l NUMBER O F POINTSFACTOR (F,,)

The factor F,, was introduced inAppendix D in the derivation ofthe uncertainty in f i x . The factor F,
itself is assumed equal to unity and is dropped from the final equations for f i x and for um,. The
relative uncertaintyin F, is called u:,,, is systematic, and is believed to have a value of 0.01 or 1% if the
specifications regarding number of points are followed. The uncertainty increases rapidly as fewer
and fewer points areused. Increasing thenumberof pointsprobably does notimprovethe
uncertainty very rapidly. There i s no random uncertainty in F,,.

E2 STEADY OPERATION FACTOR FOR X (Fsx)

The factor F,, was introduced in Appendix D in the derivation of the uncertainty in f i x . Similar
factors F,, for other performance variables X are also required. In every case, the factor itself is
assumed equal to unity and is dropped from the final equations for X and for u,. The relative
uncertainty in F,, is random, is called uRF,,, and is evaluated from thereference measurementsfor the
velocity pressure pVR,the appropriate temperature TR,and the appropriate static pressure psaR.The
evaluation is obtained as follows:
( a ) obtain averages for pvR,TR,and psaRmeasurements for each window of time;
(b) calculate h, = (psaRpVR/TR)”’for each window of time;
(c) calculate the mean and the standard deviation for all h, (¡.e., for all windows of time);
( d ) multiply the standard deviation by 2;
(e) divide by the mean; and
( f ) call the result u$$,.
Other steady operation factors are required and a similar procedurecan be used. Table E I lists the
factors, the reference measurements, and the combinations required to determineu:,,. There is no
systematic uncertainty in FSx.

E3TEST MEASUREMENTS
Typical values for both the random and the systematic components of the uncertainties in the
various test measurements are shown in Table E2.

I29

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 TABLE E I
Facfor Uncertainty Combination of Reference Measurements

TABLE E2
Random Uncertainty Systematic Uncertainty

uRA,= 0.007 usAx= 0.007

uRR = nil USR = 0.002

URTsj= 0.5OF UsTsj= 2OF

uRp. = 0.025 USPvj = 0.011

VI

uRpsj= 0.015 us = 0.011

PSI

URpb= 0.01 in. Hg USpb= 0.05 in. Hg

UROj= 20 us3 = 2O
UR3 = 20 us.$j= 20
URqM = 0.001 US,M = 0.010

0.001 digital
usw = 0.010

U~ - (0.001 digital
E USE = 0.010
E - 0.010 analog

u~ - (0.001 digital
I
’- 0.010 analog
u: = 0.010

T URr = 0.010

Pl UR,,( = 0.010 usp, = 0.010

n uR,,= I count U’,, = nil

t uR,= 2 sec -slip usl= I sec

~~ ~ ~

GENERAL NOTE:
These values should only be used if the actual circumstances support their use.

130

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 ASME P T C * 1 1 B 4 m 0757670 0051404 O W

The various randomuncertaintiesthat are listed in Table E2 are based on estimates ofthe
fluctuationsinthe measured variable during a typicalfan test (excludingfluctuationsdueto
unsteady operation as reflected in the steady operation factor).These fluctuations are due in part to
the fact that the fan has a finite number ofblades. The extent of the fluctuations willbe influenced
by the damping that operates on the signal and therefore by the choice of instruments.
The various systematic uncertainties that are listed in Table E2 are based on the assumption that
instruments will be selected for the test in accordance with the specifications in this Code. The
values shown are based on estimates of the residual uncertainty after calibration, onestimates of the
effects of temperature and other changes not included in the calibration, and on estimates of
operator bias.

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I
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 F

ASME P T C x l l €!L( M 0759b70 0 0 5 3 4 0 5 2 M

APPENDIX F
REFERENCES

(IGerhart,
) P., Jorgensen, R., and Kroll, J., “A ComparisonofTwoAlternative Methodsfor
Defining Fan Performance,” journal of Engineering for Power, January 1982.
(2) Kline, S. J . and McClintock, F. A., “Describing Uncertainties in Single-Sample Experiments,”
Mechanical Engineering, January 1953.
(3) I S 0 Standard 5168, “MeasurementofFluidFlow-Estimation ofUncertaintyof a Flow-Rate
Measurement”.
(4)ASHRAE Standard 51-75/AMCA Standard 210-74, “Laboratory Methods of Testing Fans for
Rating”.
(5) Brown, N,, “A Mathematical Evaluation of Pitot Tube Traverse Methods,” ASHRAE Paper 2325,
1975.
(6) “Draft Proposal for an I S 0 Standard: Measurement of Fluid Flow in Closed Conduits by the
Velocity Area Method Using Pitot-static Tubes,” ISO/TC-30/SC-3, February 1974.
(7) “ParticulateSampling Strategies for Large Power Plants Including Non-uniform Flow,” EPA
Report PB-257-090, June 1976.
(8) Cerhart, P., Nuspl, S., Wood, C., and Lovejoy, S., “An Evaluation of Velocity Probes for
Measuring Non-uniformGas Flow in Large Ducts,” journal ofEngineering for Power, October
1979.
(9) Gerhart, P. M. and Dorsey, M. J., “Investigation of Field Test Procedures for Large Fans,” EPRl
Report CS 1651, December 1980.
(IO) Gerhart, P. M., “Averaging Methods for Determining thePerformance of Large Fans from Field
Measurements,” journal ofEngineering for Power, April 1981.
(11) Wyler, J.
S.,“Probe Blockage Effects in Free Jetsand Closed Tunnels,”journal of Engineeringfor
Power, October 1975.
(12) Benedict, R. P., Fundamentals o f Temperature, Pressure, and Flow Measurements, 2nd Edition,
Wiley-lnterscience, 1977, pp. 356-359.
(13) Dean, R. C.,ed., Aerodynamic Measurements, MIT Cas Turbine Lab Report, 1953.
(14) Obert, E., and Caggoli, R., Thermodynamics, 2nd Edition, McGraw-Hill Book Co., 1963.
5th Edition, McGraw-Hill Book Co., 1973,
(15) Perryand Chilton, ChemicalEngineers Handbook,
PP. 3-248.
(16) “Compressibility Effects for Industrial Fans,” ISO/TC 117/SC-1, January 1982,
(17) AMCA Publication 201, Fans and Systems.
(18) Clarke, M. S., “The Implementation and Analysis of a PTC 11 TestProgram,”1982 AMCA
Engineering Conference.
(19) Yost, John G., “Field Performance Testingof Large Power Plant Fans,” MSME Thesis, University
of Akron, Akron, Ohio.
133

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 ,. . ....

PERFORMANCE TEST CODES NOW AVAILABLE

1
PTC 4.3 -AirHeaters..... ........................,..,..........,..... (1968)
PTC 23 -
Atmospheric Water Cooling Equipment.. , .. ..'. ....... .
, , , , .(1958)
PTC 8.2 -
Centrifugal Pumps , . .................. .... .. .. .... .... .. .. .(1965)
PTC 12.1 -
Closed Feedwater Heaters.. , , .. ..... .. .............. . .
,, , , , .(1978)
-
PTC 4.2 Coal Pulverizers , ....... ... . ......... ........ . ..... . .....
, , .(1969)
PTC 10 -
Compressors and Exhausters , . ................ ....... . ....
, .(1965)
ìt PTC 39.1 -
Condensate Removal Devices for Steam Systems .. .. ... . . . ..
.(1980)
P PTC 12.3 - Deaerators . .. .. .. . ... ... ... . ..... .. . . ... . . .
, ,,, ,, , , , , ,,, , ,( 1977)
PTC 2 - Definitions and Values . ........ . ... . . . ..... ..... ........
, , , .(1980)
PTC 38 - Determining the Concentration of Particulate Matter in a
Gas Stream , . .. .. . . . .. . ... .. .... ... . . . . ... . .. .
, , , , , ,, ,, , .(1980)
PTC 28 - Determining the Properties of Fine Particulate Matter .. . . . . . .
.(1965)
PTC 3.1 - Diesel and Burner Fuels., , ,,, , ... .. .. . ... . . .. .. . ..
,, ,, , , , , ,.(1958)
PTC 9 - Displacement Compressors, Vacuum Pumps and Blowers.. .(1970).. .
PTC 7.1 -DisplacementPumps.......,...... ......................... ,(1962)
PTC 21 - Dust Separating Apparatus., ,..... . . .. . ........... . .. .. . .
, , .(1941)
PTC 24 - Ejectors.. ......... ............ . .... . ............ .... . . ...
, .(1976)
PTC 14 -
Evaporating Apparatus ...*.. .. . . . ... ... .... . ....
, , , ,, , , ,, , , .(1970)
PTC 16 - Gas Producers and Continuous Gas Generators.. , . . .. ... . .
, , .(1958)
PTC 4.4 - Gas Turbine Heat Recovery Steam Generators.. ,.. . . . . . . . ...
.(1981)
PTC 22 - Gas Turbine Power Plants.. . ..... .. .. . . .. . .. . . . . . . .. . .. . .
, , .(1966)
PTC 3.3 - Gaseous Fuels , ,.. . .. .. .... . .. . . .... ... ... . . .... . .. .
,, , , , , .(1969)
PTC 1 -
General Instructions , . . .. ..... .. . ...... .. .... . .... . .... ...
, .(1980)
PTC 18 - Hydraulic Prime Movers.. , , . ..... . . . . . . ....... . . . . . . . .
, , , , , .(1949)
PTC 31 - Ion Exchange Equipment , . ..... . ..... .. ...... . . ... . . ..
, .(1973)
. . . .. . .... . ... .... . . . .. .. .... . ..
I . .

PTC 33 - Large Incinerators , , , , , , , , .(1978)

PTC 32.1 -
Nuclear Steam Supply Systems.. . . .. .... . . ...... . . .. . ,...
, . .(1969)
PTC 20.2 - Overspeed Trip Systems for Steam Turbine-Generator Units .(1965) ..
PTC 20.3 - Pressure
Units
Control
Systems
Used on
Steam Turbine-Generator
............,....................................... (1970)
' 1
PTC 18.1 - Pumping Mode of Pump/Turbines.. . . . ......... ... ...... ...
,(1978)
PTC 17 - Reciprocating Internal-Combustion Engines.. ,, ... .. ... .. . . .
, .(1973)
PTC 7 - Reciprocating Steam-Driven Displacement Pumps,. , . . ... . . ..
.(1949)
PTC 6 - Reciprocating Steam Engines., , , , , ,,. ... .... ...... .. ....
, ,, .(1949)
PTC 25.3 -
Safety and Relief Valves , , . .. ... .... . . ... ....... . .... . . . ..
, .(1976)
PTC 3.2 -SolidFuels........ ......................................... (1954)
PTC 20.1 - Speed and Load Governing Systems for Steam Turbine-
Generator Units ... ....... .. ...... . ..... ... .. . .... .. .
,, , , .(1977)
PTC 29 - Speed-GoverningSystemsforHydraulicTurbine-Generator
Units . .... . . .. . . . . . . .. ..... . .. . .... . . . . . ..
, ,, , ,, , ,, , , , , .(1965)
PTC 26 - Speed-GoverningSystemsfor Internal Combustion-Engine-
Generator Units ........ . ..... . . . ... .... . ...... .... . ..
, , , .(1962)
PTC 23.1 - Spray Cooling Systems.. , , ,,, ... . ..... . .... ..... .. .. .......... ..
, , , .(1983)
PTC 12.2 - Steam-Condensing Apparatus . .... .. . ...... .. . .. . .
, .(1983)
PTC 4.1 - Steam-Generating Units . . ;. .. ......... . . ... . . .. . ;. . . ... .
, , .(1964)
PTC 6 -
Steam Turbines ,, .. ..... .. .. . .. .. .. ... . . . . . .
,, ,, , , , , , , , , , .(1976)
PTC 6A -
Appendix A to Test Code for Steam Turbines , , . . . . .. . .... . . .
.(1982)

PTC 6 - Guidancefor Evaluationof Measurement

Report
Uncertainty in Performance Tests of Steam Turbines.. ..(1969)
PTC 6s Report - Simplified Procedures for Routing Performance Tests
. of Steam Turbines.. , . , , ..., , , ... , ..., ,, ., .. . , .. .... . .(I970)
PTC 32.2 Report - Methods of Measuring the Performance of Nuclear
Reactor Fuel in Light Water Reactors . . . .. .. .. . .. .. . . . .(1978)
I'

1
C05284

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