INSTITUTE OF AERONAUTICAL ENGINEERING

(Autonomous)
Dundigal, Hyderabad - 500 043

AERONAUTICAL ENGINEERING
QUESTION BANK

Course Title AIRCRAFT PROPULSION

Course Code AAEC07
Program B.Tech
Semester FOUR AE
Course Type Core
Regulation UG-20
Theory Practical
Course Structure Lecture Tutorials Credits Laboratory Credits
3 1 4 - -
Course Coordinator Dr. Praveen Kumar Balguri, Associate Professor

COURSE OBJECTIVES:
The students will try to learn:

I The fundamentals of air-breathing propulsion system, their operating principles, and

function of an individual component.
II The geometry of flow inlets, combustion chambers, and factors affecting their
performance.
III The establishment of flow through various inlets and nozzles under different operating
conditions.
IV The operating principles of various compressors, turbines and performance
characteristics under different flight conditions.

COURSE OUTCOMES:
After successful completion of the course, students should be able to:

CO 1 Compare the operating principles of various gas turbine engines and Understand
their components for selecting the suitable engine as per the mission
requirements.
CO 2 Utilize the thrust equation and engine cycle analysis for achieving Apply
the required performance.
CO 3 Apply the knowledge of flow through various inlets, and nozzles under Apply
various operating conditions for selecting the suitable inlets and nozzle
as per the mission requirement.
CO 4 Compare the different types of combustion chambers for identifying Understand
the design variables affecting their performance.
CO 5 Make use of the performance characteristics and efficiencies of Apply
different compressors and turbines for identifying a suitable
combination.
 CO 6 Identify the important design performance parameters of ramjet Apply
engine towards developing optimized ramjet engine.

QUESTION BANK:
MODULE I
AIR-BREATHING ENGINES
PART A-PROBLEM SOLVING AND CRITICAL THINKING QUESTIONS
Q.No QUESTION Taxonomy How does this CO’s
subsume the level
1 Air flows through a turbojet engine Apply This would require the CO 2
at the rate of 50.0 kg/s and the fuel learner to recall thrust
flow rate is 1.0 kg/s. The exhaust equation when the
gases leave the jet nozzle with a nozzle is unchoked and
relative velocity of 600m/s. when the exit pressure
Compute the velocity of the is greater than ambient
airplane, if the thrust power is 1.5 pressure, understabd
MW in the following two cases: the given variables and
1. Pressure equilibrium exists over solve for velocity of
the exit plane the airplane at the
2. If the pressure thrust is 8 kN given conditions.
2 A fighter airplane is powered by two Apply This would require the CO 1
turbojet engines. It has the learner to recall the
following characteristics during expressions for net
cruise flight conditions: thrust, speed, Te , Me
Wing area (S) = 49.24 m2 , Engine relate the given
2
inlet area Ai = 0.06 m , Cruise variables and solve for
speed Vf = 243 m/s , Flight net thrust, weight,
altitude = 35,000 ft, Drag and lift speed, static
coefficients are CD =0.045, CL =15 temperature and Me .
CD, Exhaust total temperature
To =1005K Specific heat ratio and
Specific heat at exit are γ =1.3, Cp
= 1100 J/(kgK)
It is required to calculate:
1. Net thrust
2. Weight
3. Jet speed assuming exhaust
pressure is equal to ambient pressure
if Pe =Pa
4. Static temperature of exhaust Te
5. Exhaust Mach number Me

Page 2
3 A turbojet engine is powering a Apply This would require the CO 1,
fighter airplane. Its cruise altitude learner to recall the CO 2
and Mach number are 10 km and flight speed, and
0.85, respectively. The exhaust gases propulsive efficiency
leave the nozzle at a speed of 600 expressions,
m/s and a pressure of 0.75 bar. The understand the given
outlet area of exhaust nozzle is Ae conditions, and solve
=0.24 m2 . The air mass flow rate is for specific thrust, and
40 kg/s and fuel to air ratio is 0.02. ηp .
It is required to calculate:
(a) The specific thrust (T /ma)
˙
(b) The propulsive efficiency using
the different expressions
4 A gas turbine operating at a Apply This would require the CO 1
pressure ratio of 11.314 produces learner to recall the
zero net work output when 473.35 temperature and
kJ of heat is added per kg of air. If pressure relationships
the inlet air temperature is 300 K at zero net work
and the turbine efficiency if 71%, condition, relate the
find the compressor efficiency. turbine efficiency and
solve for compressor
efficiency.
5 Boeing 747 aircraft is powered by Apply This would require the CO 1
four CF-6 turbofan engines learner to recall the
manufactured by General Electric expressions for mass
Company. Each engine has the flow rate, flight speed,
following data: specific thrust, TSFC,
Thrust force 24.0 kN, Air mass flow relate the given data,
rate 125 kg/s, Bypass ratio 5.0, Fuel and solve for the jet
mass flow rate 0.75 kg/s, Operating velocities, specific
Mach number 0.8, Altitude 10 km thrust, and TSFC.
Ambient temperature 223.2 K,
Ambient pressure 26.4 kPa, Fuel
heating value 42,800 kJ/kg, If the
thrust generated from the fan is 75%
of the total thrust, determine
(a) The jet velocities of the cold air
and hot gases
(b) The specific thrust
(c) The thrust specific fuel
consumption (TSFC)

Page 3
6 A Boeing 747 aircraft has a Apply This would require the CO 2
lift-to-drag ratio of 17. The learner to recall the
fuel-to-air ratio is 0.02 and the fuel expressions for range,
heating value is 45,000 kJ/kg. The fuel consumed at the
ratio between the weight of the trip, and weight at
aircraft at the end and start of landing, relate the
cruise is 0.673. The overall efficiency given data and solve
is 0.35. for the required
1. Calculate the range of aircraft. parameters
2. What will be the fuel consumed
in the cruise if the takeoff mass of
aircraft is 385,560 kg?
3. If the fuel consumed during the
engine start, warming, and climb is
4.4% of the initial aircraft weight
and the fuel consumed during
descent, landing, and engine stop is
3.8% of the aircraft weight at the
end of cruise, calculate the fuel
consumed in the whole trip. .
7 The airplane has turbojet engine Apply This would require the CO 2
which produces 12.12 KN thrust at learner to recall the
an altitude of 9150 m, where the thrust, pressure ratio,
ambient conditions are 32 kPa and fuel-to-air ratio,
240 K. The pressure ratio across the exhaust velocity, and
compressor is 12 and temperature at mass flow rate
the turbine inlet is 1400 K. The relationships,
aircraft speed is 310 m/s. Assume understand the given
ideal operation for all components; data and conditions,
assume un-choked nozzle and solve for the required
constant specific heat in all parameters
processes, Cp = 1005 J/kgK. The
heating value of the fuel is 42,700
kJ/kg. Determine (a) The
fuel-to-air ratio
(b) The velocity of the exhaust gases
(c) The air mass flow rate
8 An aircraft having ideal turbojet Apply This would require the CO 1
engine flying at an altitude where learner to recall the T
the ambient conditions are 0.458 bar & P relationships at
and 248 K. Speed of the aircraft: intake, compressor,
805 km/h, Compressor pressure energy balance of
ratio: 4:1, Turbine inlet combustion chamber,
temperature: 1100 K, Nozzle outlet work, relate the given
area 0.0935 m2 , Heat of reaction of conditions and data,
the fuel: 43 M J/kg. Find the thrust solve for thrust and
and TSFC assuming cp as 1.005 TSFC.
kJ/kgK and γ as 1.4

Page 4
9 A comparison between turbojet and Apply This would require the CO 2
turbofan engines is considered here. learner to recall the
Both the engines have the same gas thrust, ηp expressions
generator (compressor, combustion for the turbo jet, turbo
chamber, and turbine). It is
fan air crafts, relate
required to calculate both the thrust
and propulsive efficiency of them them with the given
provided the following data: conditions, data, solve
for the thrust and
Turbo Turbo propulsive efficiency.
Engine
jet fan
core air
mass
20 20
flow
rate (Kg/s)
Bypass
0 5
ratio
Flight
speed 1100 1100
(Km/hr)
Fuel to
0.02 0.015
air ratio
Exhaust
speed for
3000 2000
hot gases
(Km/hr)
Exhaust
speed for
cold 0 1460
stream
(Km/hr)

10 DASSAULT MIRAGE G is a two Apply This would require the CO 2

seat Strike and Reconnaissance learner to recall the
fighter powered by one SNECMA specific thrust, TSFC
TF-306C turbofan engine. It has the and ηp expressions,
following characteristics: Flight relate the given data,
Mach number 0.8, Altitude 65,000 conditions, solve for
ft, Ambient temperature 216.7 K specific thrust, TSFC,
Ambient pressure 5.5 kPa, Fuel and propulsive
heating value 42,700 kJ/kg Thrust efficiency.
force 53.4 kN, Air mass flow rate 45
kg/s, Fuel mass flow rate 2.5 kg/s
Aircraft gross weight (65,000 ft) 156
kN, Aircraft takeoff weight 173.3 kN
Wing area 26.4 m2 , Fuel weight 5.
kN, Maximum lift coefficient CL
max=1.8 CD0 = 0.012 K1 = 0.2 K2
= 0.0, Air density at take-off 1.225
kg/m3 Air density at 650,000 ft 0.88
kg/m3 , Calculate:
1. The specific thrust
2. TSFC
3. The propulsive efficiency

Page 5
 Part - B (Long Answer Questions)
1 Compare turboprop, turbofan, and Understand This would require the CO 1
turbojet engines with necessary learner to recall the
diagrams. components of
turboprop, turbofan,
and turbojet engines
and compare them
based on components
and operating
principles.
2 Illustrate the ramjet and scramjet Understand This would require the CO 1
engines and highlight their learner to recall the
differences based on principle of components of ramjet
operation. and scramjet engines
and compare them
based on components
and operating
principles.
2 Illustrate the ramjet and scramjet Understand This would require the CO 1
engines and highlight their learner to recall the
differences based on principle of components of ramjet
operation. and scramjet engines
and compare them
based on components
and operating
principles.
3 Explain in detail the functions of all Understand This would require the CO 1
the major components in the learner to recall the
turbojet engine. operation of turbojet
engine, and explain the
roles of individual
component.
4 Derive the thrust equation for ideal Apply This would require the CO 2
turbojet engine. learner to recall the
conditions of ideal
turbojet engine,
understand the change
in momentum of the
system, and develop
the thrust equation.
5 Illustrate the working principle of a Understand This would require the CO 1
scramjet learner to recall the
components of a
scramjet engine and
explain the roles of all
the components for the
operation of scramjet.

Page 6
6 Outline the performance parameters Understand This would require the CO 2
of gas turbine engine and give an learner to recall the
equation for any one performance characteristic, function,
parameter. and requirement or
design basis of a gas
turbine engine and
outline the quantified
performance
parameters of gas
turbine engine.
7 Explain the need for an air Understand This would require the CO 2
breathing engine? learner to recall the
difference between an
air-breathing engine
and a non-air-breathing
engine, explain the role
of an air-breathing
engine in
transportation
worldwide.
8 Derive the expressions for isentropic Apply This would require the CO 2
efficiencies of a simple turbojet learner to recall the
engine. ideal performance of
turbojet engine and
explain the isentropic
efficiencies of individual
component and develop
the expressions for
isentropic efficiencies
for a simple jet engine.
9 Illustrate the working principle of a Understand This would require the CO 1
turbofan engine. learner to recall the
components of a
turbofan engine and
explain the roles of all
the components for the
operation of turbofan.
10 Explain in detail the working of a Understand This would require the CO 1
ramjet engine. Also, compare with a learner to recall the
scramjet engine. operation of ramjet
engine, and explain the
roles of individual
component, and
explain how a ramjet
engine is different from
a scramjet engine.

Page 7
11 Illustrate the working principle of a Understand This would require the CO 1
turboprop engine, and compare with learner to recall the
a turbofan engine. turboprop engine, and
compare the roles of
individual component
of turboprop with that
of turbofan engine.
12 Explain the various factors that Understand This would require the CO 2
affecting the engine thrust with neat learner to recall the
sketch. thrust equation and
explain how various
factors affects the
thrust.
13 Compare ram jet and turbojet Understand This would require the CO 1
engines mentioning their advantages learner to recall the
and disadvantages. components of ramjet,
and turbojet engines
and compare them
based on components
and operating
principles.
14 Explain the flight limit and Understand This would require the CO 1
operational limits for different learner to recall the
engines with neat sketch. operation profile of
different aircraft
engines, explain their
flight and operational
limits using Mach
number and altitude.
15 Compare air-breathing, Understand This would require the CO 1
non-air-breathing engines and a gas learner to recall the
generator. major components of
air-breathing,
non-air-breathing
engines, and a gas
generator, compare
them based on their
operating principles.
16 Explain in detail about variation of Understand This would require the CO 1
pressure, temperature and velocity learner to recall how
across turbojet engine with the help the pressure,
of a neat plot. temperature and
velocity vary through
the inlet, compressor,
combustion chamber
and nozzle during the
operation, compare
them with neat sketch.
17 What are the advantages and Remember — CO 1
disadvantages of turbojet, turbo
prop and turbo fan engines.

Page 8
18 Explain the need for after burner? UnderstandThis would require the CO 1
Draw and explain the T-S diagram learner to recall the
for turbojet engine with and without components and
after burner cycle. working of afterburner,
and explain
temperature-entropy
curve for turbojet with
respect to afterburner
19 Explain combined cycle engine with Understand This would require the CO 2
a neat sketch. learner to recall the
combined cycle engines
and explain the
components and
working principle.
20 Develop the equation for propulsive Apply This would require the CO 2
efficiency and explain the reason for learner to recall the
turbofan having better propulsive definition of propulsive
efficiency. efficiency and
understand Wout and
T, and develop
equation for propulsive
efficiency, and give the
reason for turbofan
better efficiency.
PART C - SHORT ANSWER QUESTIONS
1 What are the different types of gas Remember — CO 1
turbine engine?
2 Compare ramjet and turbojet Understand This would require the CO 1
engine. learner to recall the
basic components of
ramjet and turbojet
and compare the
operating principles.
3 What is the type of engine that Remember — CO 1
would be used in a helicopter?
4 Compare turboprop with a turbojet Remember This would require the CO 1
engine? learner to recall the
basic components of
turboprop and turbojet
and compare the
operating principles.
5 What is the type of engine that Remember — CO 1
powers most of today’s airliners and
why?
6 Compare ramjet and scramjet Understand This would require the CO 1
engine? learner to recall the
basic components of
ramjet and scramjet
and compare the
operating principles
7 Define bypass ratio. Remember — CO 1

Page 9
 8 Interpret thermal efficiency. Understand This would require the CO 2
learner to recall the
different efficiencies of a
propulsions system and
explain how to measure
thermal efficiency.
9 Define propulsive efficiency. Remember — CO 2
10 Derive the thrust equation for a Apply This would require the CO 2
simple turbojet engine. learner to recall the
momentum equation,
understand the change
in momentum flux, and
develop thrust
equation.
11 Define specific thrust. Remember — CO 2
12 Explain specific fuel consumption. Remember This would require the CO 1
learner to recall the
rate of fuel, thrust
produced, and explain
SFC.
13 Define specific impulse. Remember — CO 1
14 What is the need for after burner? Remember — CO 2
15 Compare turboprop and turbojet Understand This would require the CO 1
engine? learner to recall the
basic components of
turbojet and turboprop
and compare the
operating principles of
both engines.
16 What is air-breathing engine? Remember — CO 1
17 What is non-air breathing engine? Remember — CO 1
18 Outline the factors that affect the Understand This would require the CO 2
engine thrust? learner to recall the
engine performance
parameters and outline
the variables that affect
the thrust.
19 Why turbo fan has better propulsive Remember — CO 2
efficiency?
20 Explain combined cycle engine? Understand This would require the CO 2
learner to recall the
operation of combined
cycle engine and
explain TBCC and
TRCC.
MODULE II
INLETS AND COMBUSTION CHAMBERS
PART A-PROBLEM SOLVING AND CRITICAL THINKING QUESTIONS
Q.No QUESTION Taxonomy How does this CO’s
subsume the level

Page 10
1 A turbofan engine during ground Apply This would require the CO 3
ingests airflow at the rate of ṁ∞ = learner to recall the
500 kg/s through an inlet area (A1) mass flow rate
of 3.0 m2 . If the ambient conditions expression and
(T∞ , P∞ ) are 288 K and 100 kPa, understand the
respectively, calculate the area ratio conditions when
(A∞ /A1) for different free stream capture area is equal to
Mach numbers. What is the value of the inlet area and solve
the Mach number where the capture for Mach number.
area is equal to the inlet area? Draw
the air stream tube for different
Mach numbers (0.2,0.4, 0.6, 0.8, 1.0,
1.2).
2 An aircraft powered by turbo fan Apply This would require the CO 3
engine flying at a Mach number of learner to recall the
0.9 and altitude of 11 km where the total pressure formulae,
ambient temperature and pressure show static pressure at
are respectively −56.50 C and inlet entry, apply the
22.632 kPa. The mass ingested into given data to calculate
the engine is now 235kg/s. If the the capture area, static
diffuser efficiency is 0.9 and the pressures at the inlet
Mach number at the fan face is 0.45, and fan face.
calculate the following:
1. The capture area
2. The static pressures at the inlet
and fan face
3 Explain about stall in subsonic Understand This would require the CO 3
inlets and their effect on engine learner to recall the
performance. stall phenomenon in
subsonic inlets and
explain the effect of
stall on the engine
performance.
4 Explain Understand This would require the CO 4
1. Pressure loss learner to recall the
2. Combustion efficiency expressions for pressure
3. Isentropic efficiency of a diffuser loss, combustion
4. Combustion instability efficiency, isentropic
efficiency, and
combustion instability
and explain the
mentioned parameters.
5 Classify combustion chambers and Understand This would require the CO 5
elaborate on each type of learner to recall the
combustion chamber with specific operation of
features. combustion chambers
and explain different
combustion chambers
based on their features.

Page 11
6 Explain about internal compression, Understand This would require the CO 3
external compression and mixed learner to recall the
compression supersonic inlet with different compression
neat sketch. mechanics in supersonic
inlets, explain the
phenomenon of
internal, external and
mixed compressions.
7 An aircraft flies at a Mach number Apply This would require the CO 3
of 0.75 ingesting an airflow of 80 learner to recall the
kg/s at an altitude where the total temperature
ambient temperature and pressure formulae, show static
are 222 K and 10 kPa, respectively. pressure at inlet entry,
The inlet design is such that the apply the resultant
Mach number at the entry to the values into static
inlet is 0.60 and that at the pressure at inlet and
compressor face is 0.40. The inlet compressor expressions
has an isentropic efficiency of 0.95. to calculate area of the
Find (a) the area of the inlet entry inlet, inlet pressure
(b) the inlet pressure recovery recovery, and the
(c) the compressor face diameter. compressor face
diameter.
8 An aircraft powered by turbo fan Apply This would require the CO 3
engine flying at a Mach number of learner to recall the
0.9 and altitude of 11 km where the isentropic equations in
ambient temperature and pressure terms of pressure, and
are respectively -56.50 C and 22.632 speed relation u2 ,
kPa. The mass ingested into the understand the given
engine is now 235 kg/s. If the data, and solve for air
diffuser efficiency is 0.9 and the speed and pressure
Mach number at the fan face is 0.45, recovery.
calculate the following:
1.The air speed at the same stations
2.The diffuser pressure recovery
factor
9 Explain Understand This would require the CO 4
1.Combustion stability learner to recall the
2. Combustion intensity combustion mechanism
and explain the
importance of
combustion stability
and intensity.

Page 12
10 An aircraft powered by turbo fan Apply This would require the CO 3
engine flying at a Mach number of learner to recall the
0.8 and altitude of 11 km where the isentropic equations in
ambient temperature and pressure terms of pressure, and
0
are respectively -55.5 C and 23.32 speed relation u2 ,
kPa. The mass ingested into the understand the given
engine is now 250kg/s. If the data, and solve for air
diffuser efficiency is 0.89 and the speed and pressure
Mach number at the fan face is 0.50, recovery.
calculate the following:
1.The air speed at the same stations
2.The diffuser pressure recovery
factor
Part - B (Long Answer Questions)
1 Illustrate the subsonic inlets and Understand This would require the CO 3
modes of operation with neat sketch. learner to recall the
various inlets, describe
the function, and the
operation of subsonic
inlets.
2 Explain the purpose of nacelle and Understand This would require the CO 3
illustrate the subsonic inlet learner to recall the
nomenclature. necessity of nacelle,
subsonic inlets for
aircraft engine and
explain the function of
inlets with help of a
neat sketch.
3 Explain isentropic efficiency of a Understand This would require the CO 3
diffuser. Does the change in learner to recall the
enthalpy change the kinetic energy? performance
Justify. parameters of a
diffuser, explain the
isentropic efficiency of
a diffuser considering
enthalpy, and kinetic
energy.
4 Explain the starting problem in Understand This would require the CO 3
supersonic inlets. Are the problems learner to recall the
predominant in any other forms of operation of supersonic
inlet? inlets and explain the
starting problem
comparing other type
of inlets.
5 Explain the shock swallowing by Understand This would require the CO 3
area variation and the adverse learner to recall the
effects of shocks? inlet nomenclature and
oblique shock waves,
and explain the shock
swallowing by area
variation of inlets.

Page 13
6 Compare different types of Understand This would require the CO 4
combustion chambers with necessary learner to recall the
diagrams. function of a
combustion chamber in
an aircraft engine,
explain the operation,
and the advantages of
different combustion
chambers.
7 Explain the factors influencing Understand This would require the CO 4
combustion chamber design. learner to recall the
role of a combustion
chamber in an aircraft
engine and explain the
factors influencing the
performance of a
combustion chamber.
8 Explain the combustion process Understand This would require the CO 4
considering the stoichiometric ratio. learner to recall the
role of a combustion
chamber in an aircraft
engine, definition of
stoichiometric ratio,
and explain the
combustion process in
different zones of
combustion chamber
considering the
influence of
stoichiometric ratio.
9 Illustrate the function of each Understand This would require the CO 4
component in gas turbine learner to recall the
combustion chamber. operation,
nomenclature of
combustion chamber of
a gas turbine engine,
and explain them with
a neat sketch.
10 Explain the flammability and Understand This would require the CO 4
combustion process of a fuel using learner to recall the
equivalence ratio. definition of
equivalence ratio,
explain how the
equivalence ratio
influences combustion
process, and
flammability of a fuel.

Page 14
11 Explain in short about the Understand This would require the CO 4
combustion efficiency and main learner to recall the
burner design parameters. definition of
combustion efficiency,
combustion chamber
deign parameters, and
explain how they affect
the performance of a
combustion chamber.
12 Explain the performance parameters Understand This would require the CO 4
of a combustion chamber. learner to recall the
combustion efficiency,
pressure loss, exit
temperature profile,
and ignition, and
explain how they affect
the performance of a
combustion chamber.
13 Explain Understand This would require the CO 3
(i) Inlet total pressure ratio learner to recall the
(ii) Inlet sizing definition of inlet total
(iii) Inlet flow distortion. pressure ratio (Πd ),
throat diameter (dt ),
the concept of inlet
flow distortion and
explain how they are
related to Mach
number and pressure.
14 Explain in detail about types of flow Understand This would require the CO 3
in straight-walled diffusers with a learner to recall the
labeled sketch. function of diffuser in
the inlet and explain
well-behaved flow, large
transitory stall, steady
stall, and jet flow in
the diffuser.
15 Outline the combustion stability of a Understand This would require the CO 4
gas turbine engine. learner to recall the
definition of
combustion stability,
combustor loading
parameter, and explain
the combustor loading
parameter.
16 Explain the flame tube cooling and Understand This would require the CO 4
fuel injection. learner to recall the
problems of combustion
systems, explain how
the flame tube cooling,
and good fuel injection
are achieved.

Page 15
17 Describe about the isentropic Understand
This would require the CO 4
efficiency of a diffuser, and stall in learner to recall the
the diffuser. definition of isentropic
efficiency, and flow
types in the diffuser
and explain ηd , and
large transitory stall,
and steady flows in the
diffuser.
18 Describe about operational modes of Understand This would require the CO 4
supersonic inlet with neat sketch. learner to recall the
supersonic inlet , and
explain the operational
modes of supersonic
inlet.
19 Explain Understand This would require the CO 3
(i) Podded intake learner to recall the
(ii) Integrated intake function of an intake in
(iii) Flush intake the gas turbine engine,
explain the asked
subsonic intakes, and
issues with them.
20 Illustrate the performance Understand This would require the CO 3
characteristics of subsonic inlet learner to recall the
during take-off and cruise. intake operation of an
aircraft engine and
explain performance of
subsonic inlet
considering mass flow,
speed and TS
diagrams.
PART C - SHORT ANSWER QUESTIONS
1 What is the function of diffuser? Remember —- CO 3
2 Illustrate the operating conditions of Remember This would require the CO 3
subsonic inlet. learner to recall the
different inlets and
explain the operating
conditions of subsonic
inlet.
3 List some of major design variables Remember —- CO 3
for the inlet.
4 Explain about inlet flow distortion. Understand This would require the CO 3
learner to recall the
inlet flow conditions
and explain the causes
and consequences of
inlet flow distortion.
5 Write typical modes of supersonic Remember —- CO 3
inlet operation.
6 What is mean by buzz? Remember —- CO 3

Page 16
7 Classify the types of combustion Understand This would require the CO 4
chamber. learner to recall the
function of combustion
chamber in jet engine,
and explain about
different types of
combustion chambers
based on mission
requirements.
8 What are all the major components Remember —- CO 4
of combustion chamber?
9 Differentiate annular and cannular Understand This would require the CO 4
type combustion chambers. learner to recall the
different types of
combustion chambers
and compare the
components and
operation of annular
and cannular type
combustion chambers
10 What is the function of fuel injector? Remember —- CO 4
11 Describe about flame holder and its Remember —- CO 4
function.
12 Compare different types of subsonic Understand This would require the CO 3
inlets. learner to recall the
various subsonic inlets
and compare the
components and
operating principles.
13 Define stoichiometric ratio. Remember —- CO 4
14 Define equivalence ratio. Remember —- CO 4
15 Classify supersonic inlets. Understand This would require the
learner to recall the
different supersonic
inlets and classify them
based on design
variables.
16 Define combustion intensity. Remember —- CO 4
17 What is the function of swirl vanes Remember —- CO 4
in combustion chamber?
18 Explain the function of liner in Understand This would require the CO 4
combustion chamber? learner to recall the
operation of
combustion chamber
and explain how liner
can increase the
performance of a
combustion chamber.
19 Define combustion efficiency. Remember —- CO 4

Page 17
 20 Compare different types of internal Understand This would require the CO 3
flow in straight walled diffuser. learner to recall the
flow, operation of
diffuser and compare
different types of
internal flow in straight
walled diffuser.
MODULE III
NOZZLES
PART A-PROBLEM SOLVING AND CRITICAL THINKING QUESTIONS
Q.No QUESTION Taxonomy How does this CO’s
subsume the level
1 A turbojet engine powering an Apply This would require the CO 3
aircraft flying at an altitude of learner to recall the
11,000m where Ta = 216.7K and Pa operation of nozzle,
= 24.444 kPa. The flight Mach understand the flow
number is 0.9. The inlet conditions property variation ,
to the nozzle are 1000 K and 60 and apply them to
kPa. The specific heat ratio of air calculate the thrust.
and gases at nozzle are 1.4 and 4/3.
The nozzle efficiency is 0.98.
Determine the thrust per inlet
frontal area for C-D nozzle.
2 Derive the equation for mass flow Apply This would require the CO 3
rate across nozzle as function of learner to recall the
Mach number, total pressure and operation of nozzle,
total temperature and get the understand the flow
equation for maximum mass flow property variation, and
rate. develop the governing
equation for nozzle.
3 Derive area ratio and Mach number Apply This would require the CO 6
relation for convergent-divergent learner to recall the
nozzle by assuming chocked operation of nozzle,
condition. understand the flow
property variation, and
develop the area ratio
and Mach number
relation for nozzle at
the given condition.
4 Prove that the force developed by Apply This would require the CO 3
thrust reversal during landing is learner to recall the
given by operation of nozzle,
F = ṁa [(1 + f )Vj cos β + Vf ] understand the need
for thrust reversal, and
construct the thrust
equation.

Page 18
5 A turbojet engine operates at an Apply This would require the CO 3
altitude where the ambient learner to recall the
temperature and pressure are 216.7 operation of nozzle,
K and 24.444 kPa, respectively. The understand the
flight mach number is 0.9 and the governing equation,
inlet conditions to the convergent and apply them to
nozzle are 1000 K and 60 kPa. If the calculate nozzle exit
nozzle efficiency is 0.98, the ratio of pressure.
specific heat is 1.33, determine
whether the nozzle is operating
under choked condition or not.
Determine the nozzle exit pressure.
6 A De Laval nozzle has to be Apply This would require the CO 3
designed for an exit Mach number of learner to recall the
1.5 with an exit diameter of 200 operation of nozzle,
mm. Find the required ratio of exit understand the
area to throat area. The reservoir governing equation,
conditions are given as p0 =1 atm apply them to calculate
T0 = 20 0 C. Find the maximum maximum mass flow
mass flow rate through the nozzle. rate, exit pressure, and
What will be the exit pressure and temperature.
temperature?
7 Derive equation for nozzle efficiency Apply This would require the CO 3
and explain in detail, the losses in learner to recall the
the nozzle, undermining the flow in nozzle,
nomenclature. understand the losses,
and develop the
equation for nozzle
efficiency.
8 An aircraft which is flying at an Apply This would require the CO 3
altitude of 10,000m, is powered by a learner to recall the
turbojet engine. where Ta = 218K governing equations of
and Pa = 25kPa. The flight Mach nozzle flow, understand
number is found to be 0.92. The the given data,
inlet conditions to the nozzle were conditions, and apply
found to be 1010 K and 58kPa. The them to calculate
specific heat ratio of air and gases at thrust per inlet frontal
nozzle are 1.4 and 4/3. The nozzle area.
efficiency is 0.98. Find the thrust
per inlet frontal area for C-D nozzle.
9 Explain flow properties variation Understand This would require the CO 3
across convergent and divergent learner to recall the
ducts using area velocity relation nozzle properties, and
with neat sketch. explain their variation
across it using area
velocity relation.

Page 19
10 The idling turbojet engines of a Apply This would require the CO 3
landing airplane produce forward learner to recall the
thrust when operating in a normal governing equations of
manner, but they can produce nozzle flow, understand
reverse thrust if the jet is property the given data,
deflected. Suppose that, while the conditions, and apply
aircraft rolls down the runway at them to calculate
100 mph, the idling engine consumes thrust.
air at 100 lbm/s and produces an
exhaust velocity of 450 f t/s.
(a) What is the forward thrust of
the engine?
(b) What is the magnitude and
direction (forward or reverse) if the
exhaust is deflected 900 and if the
mass flow is kept constant?
Part - B (Long Answer Questions)
1 Explain the flow through convergent Understand This would require the CO 6
nozzle and plot the variation of learner to recall the
pressure and velocity. nozzle flow, and explain
the flow through
convergent nozzle.
2 Illustrate the thrust vectoring with a Understand This would require the CO 3
labeled diagram showing the various learner to recall the
thrust vectoring methods. thrust vectoring
nozzles, explain the
purpose, and methods
of thrust vectoring.
3 Illustrate the nozzle choking and the Understand This would require the CO 3
conditions with a labeled diagram, learner to recall the
nozzle flow, and explain
the condition when
choking takes place.
4 Explain Understand This would require the CO 3
1. Cone learner to recall the
2. Bell types of nozzles and
3. Annular convergent divergent explain the operation
nozzle and flow through cone,
bell and annular CD
nozzle.
5 Derive area velocity relation by Apply This would require the CO 3
assuming quasi-one dimensional flow learner to recall the
through a passage. nozzle flow, and
understand quasi-one
dimensional flow
conditions, and develop
area velocity relation.

Page 20
6 Explain the operating conditions of Understand This would require the CO 3
convergent-divergent nozzle with a learner to recall flow
labeled diagram. through nozzles and
explain the flow
through CD nozzle
with a neat sketch.
7 Explain various methods used for Understand This would require the CO 6
thrust reversal, with a labeled learner to recall the
diagram for each process. types and functions of
nozzles and explain the
role of nozzle in
braking.
8 Explain different technique available Understand This would require the CO 3
for producing variable Mach number learner to recall the
at the nozzle exit. flow through nozzle,
explain the need and
methods of achieving
variable Mach number
at the nozzle exit.
9 Explain thrust vectoring with a Understand This would require the CO 3
necessary diagram. learner to recall the
thrust vectoring nozzles
and explain the
purpose and methods
of thrust vectoring
10 Explain about various methods used Understand This would require the CO 3
for thrust reversal with a labeled learner to recall the
diagram for each method. types and functions of
nozzles and explain the
role of nozzle in
braking.
11 Illustrate the theory of flow through Understand This would require the CO 6
convergent-divergent nozzle and plot learner to recall the
the variation of pressure and nozzle flow, explain the
velocity. flow through
convergent nozzle with
the help of P, V plot.
12 Describe the theory of flow in Understand This would require the CO 3
isentropic nozzle and the working learner to recall the
principle of the nozzle. flow in nozzles and
explain the working
principle and flow in
nozzles.
13 Explain whether a fixed area Understand This would require the CO 3
convergent-divergent nozzle can learner to recall the
deliver different Mach number flow. purpose and features of
CD nozzle, and explain
the flow through fixed
area CD nozzle.

Page 21
14 Explain how over-expanded Understand
This would require the CO 3
operating condition is possible for learner to recall the
convergent nozzle. flow in nozzles and
explain over-expanded
operating condition
15 Will there be any wave formation in Understand This would require the CO 3
correctly expanded nozzle. Justify learner to recall the
your answer. flow in nozzles and
explain
correctly-expanded flow
conditions.
16 Explain the condition for Understand This would require the CO 3
convergent-divergent nozzle to learner to recall the
deliver supersonic Mach number? flow in nozzles and
explain the flow in CD
nozzles.
17 Brief about the theory of flow Apply This would require the CO 6
through nozzle and derive an learner to recall the
equation for the showing the flow flow in nozzles, explain
through nozzle. the working principle,
flow in nozzles, and
develop expression for
flow in nozzle.
18 Illustrate the nozzle choking, and Understand This would require the CO 3
the conditions with a labeled learner to recall the
diagram. nozzle flow, and explain
the condition when
choking takes place.
19 Derive an equation for the flow Apply This would require the CO 3
through nozzle and explain flow learner to recall the
through CD nozzle with a diagram. flow in nozzles and
explain the working
principle and flow in
CD nozzles and develop
expression for flow in
nozzle.
20 How is thrust reversal achieved? Is Understand This would require the CO 3
thrust vectoring similar to thrust learner to recall the
reversal? Justify your answer. flow in nozzles and
compare thrust reversal
and thrust vectoring.
PART C - SHORT ANSWER QUESTIONS
1 Define nozzle. Remember — CO 3
2 Explain the reason for formation of Understand This would require the CO 3
expansion fan at nozzle exit during learner to recall the
under-expanded condition. nozzle flow and explain
the reason for forming
expansion fan for
under-expanded
condition.
3 Write types of nozzle. Remember — CO 3

Page 22
4 List any three requirements a nozzle Remember — CO 3
should fulfill.
5 Describe correctly expanded nozzle. Understand This would require the CO 3
learner to recall the
types of nozzles and
explain the correctly
expanded nozzle
6 What is the condition for nozzle Remember — CO 3
choking?
7 What is the maximum Mach Remember — CO 3
number a convergent nozzle can
deliver and why?
8 Define characteristics Mach number. Remember — CO 3
9 Describe under-expanded nozzle. Remember This would require the CO 3
learner to recall the
types of nozzles and
explain the
under-expanded nozzle.
10 Define thrust vectoring? Remember — CO 3
11 Why oblique shock form at nozzle Remember — CO 3
exit during over-expanded
condition?
12 What is the need for variable area Remember — CO 3
nozzle?
13 Describe over-expanded nozzle. Understand This would require the CO 3
learner to recall the
types of nozzles and
explain the
over-expanded nozzle
14 Write different techniques used to Remember — CO 3
create variable area nozzle.
15 Describe about thrust reversal. Remember — CO 3
16 Explain the need for thrust reversal? Understand This would require the CO 3
learner to recall the
types and functions of
nozzles and explain the
role of nozzle in
braking.
17 What is the need for variable area Remember — CO 3
nozzle?
18 Define isentropic efficiency of nozzle. Remember — CO 3
19 Explain nozzle choking? Understand This would require the CO 3
learner to recall the
nozzle flow, and explain
the condition when
choking takes place.
20 Plot the variation of pressure and Remember — CO 3
velocity across chocked C-D nozzle.

Page 23
 MODULE IV
COMPRESSORS
PART A-PROBLEM SOLVING AND CRITICAL THINKING QUESTIONS
Q.No QUESTION Taxonomy How does this CO’s
subsume the level
1 The following data are suggested as Apply This would require the CO 5
a basis for the design of a learner to recall
single-sided centrifugal compressor: governing equations of
Power input factor c 1.04, Slip factor centrifugal compressor,
s 0.9. Rotational speed N 290 rev/s, interpret the given
Overall diameter of impeller 0.5 m data, conditions, and
Eye tip diameter 0.3 m, Eye root apply them to calculate
diameter 0.15 m. Air mass flow m 9 the pressure ratio,
kg/s, Inlet stagnation temperature power, and inlet angle.
T01 295 K Inlet stagnation pressure
p01 1.1 bar, Isentropic efficiency hc
0.78.
(a) determine the pressure ratio of
the compressor and the power
required to drive it assuming that
the velocity of the air at the inlet is
axial;
(b) to calculate the inlet angle of the
impeller vanes at the root and tip
radii of the eye, assuming that the
axial inlet velocity is constant across
the eye annulus
2 Derive the equation for work done Apply This would require the CO 5
and pressure rise across centrifugal learner to recall the
compressor operation of
compressor, illustrate
the velocity triangle,
and use them to build
governing equation for
compressor.
3 Explain in details about the Understand This would require the CO 5
methods used to control surge. Also learner to recall the
differentiate between stall and surge concept of surge, and
in a compressor. explain the method to
control it.
4 Derive the equation for stage Apply This would require the CO 5
efficiency. What are the advantages learner to recall the
of centrifugal flow compressor over operation, flow in
the axial flow compressor? Justify compressor, illustrate
with appropriate reasoning. the velocity triangle,
and use them to build
stage efficiency
equation for
compressor.

Page 24
5 Illustrate the operation of axial flow Understand This would require the CO 5
compressor with a labeled diagram. learner to recall the
components of
compressor, illustrate
their function.
6 A basis for the design of a Apply This would require the CO 5
single-sided centrifugal compressor learner to recall
gave the following data of power governing equations of
input factor c 1.03, slip factor s 0.9, compressor, interpret
rotational speed N 285 rev/s, overall the given data,
diameter of impeller 0.4 m, eye tip conditions, and apply
diameter 0.3 m, eye root diameter them to calculate the
0.15 m, air mass flow ṁ 10 kg/s, pressure ratio, power,
inlet stagnation temperature T01 and inlet angle.
296 K, inlet stagnation pressure p,
12 bar, isentropic efficiency hc 0.79.
Determine the following:-
(a) Pressure ratio of the compressor
(b) the power required to drive it
assuming that the velocity of the air
at the inlet is axial
(c) The inlet angle of the impeller
vanes at the root and tip radii of the
eye, assuming that the axial inlet
velocity is constant across the eye
annulus
7 Derive the equation for work done Apply This would require the CO 5
and pressure rise across centrifugal learner to recall the
compressor. operation of centrifugal
compressor, illustrate
the velocity triangle,
develop the equation
for work done, and
pressure rise.
8 Define slip factor and obtain an Apply This would require the CO 5
equation along a labeled diagram learner to recall the
showing the compressor staging. concept of slip, explain
the reason for slip and
build the governing
equation.
9 Derive the equation for blade Apply This would require the CO 5
efficiency of a compressor and the learner to recall the
stage efficiency of a compressor. operation of
compressor, illustrate
the velocity triangle,
develop the equation
for blade efficiency of a
compressor and the
stage efficiency

Page 25
10 Explain in detail about the Understand This would require the CO 5
compressor cascade with a neat and learner to recall the
labeled diagram. compressor cascade,
and explain their
application.
Part - B (Long Answer Questions)
1 Explain the principle of operation of Understand This would require the CO 5
centrifugal compressor and illustrate learner to recall the
a labeled diagram of a compressor. types and role of the
compressor, interpret
the principle of
operation of centrifugal
compressor.
2 Explain about basic operation of Understand This would require the CO 5
axial flow compressor and illustrate learner to recall the
a labeled diagram of a compressor. types and role of the
compressor, interpret
the principle of
operation of axial flow
compressor.
3 Explain about factors affecting stage Understand This would require the CO 5
pressure ratio. Do you think that learner to recall the
stage pressuring ratio is needed? operation of
compressor, interpret
the factors affecting
stage pressure ratio.
4 Explain Understand This would require the CO 5
(a) Advantages of centrifugal learner to recall the
compressor over axial flow types and role of the
compressor. compressor, explain the
(b) Advantages of axial flow advantages of both
compressor over centrifugal compressors.
compressor.
5 Illustrate the velocity diagram of Understand This would require the CO 5
axial and centrifugal compressor, learner to recall the
and neatly label each part. operation of
compressor, illustrate
the velocity triangle.
6 Explain the performance Understand This would require the CO 5
characteristics of axial and learner to recall the
centrifugal compressor. operation of
compressor, explain the
performance
characteristics of both
compressors.
7 Explain Understand This would require the CO 5
(a) Compressor stall learner to recall the
(b) Surge operation and flow in
(c) Rotating stall. compressor, explain the
compressor stall, surge,
and rotating stall.

Page 26
8 Explain about the methods used to Apply This would require the CO 5
control surge. Also differentiate learner to recall the
between stall and surge in a concept of surge in
compressor. compressor, explain the
methods to control,
differentiate stall and
surge.
9 Explain in brief the functions of the Understand This would require the CO 5
components in a centrifugal learner to recall the
compressor with a diagram operation and flow in
compressor, explain the
functions of the
components in a
centrifugal compressor.
10 Explain the variation of enthalpy, Understand This would require the CO 5
pressure, temperature across stator learner to recall the
and rotor of axial flow compressor operation and flow in
with neat sketch. axial compressor,
explain the enthalpy,
pressure, temperature
across stator and rotor.
11 What do you understand by surge in Understand This would require the CO 5
compressor? Is it similar to chocking learner to recall the
condition in the compressor? Justify operation and flow in
compressors, and
explain surge and
choke.
12 Define slip factor. Obtain an Apply This would require the CO 5
equation along a labeled diagram learner to recall the
showing the compressor staging. concept of slip factor,
explain the reason for
slip and build the
governing equation.
13 Define hysteresis. Does it relate to Understand This would require the CO 5
stall in a compressor? Justify your learner to recall the
answer with suitable reasoning. operation and flow in
compressor, and
explain stall and
hysteresis.
14 What are the advantages of Understand This would require the CO 5
centrifugal flow compressor over the learner to recall the
axial flow compressor? Justify with operation and flow in
appropriate reasoning. axial and centrifugal
compressors, compare
them.

Page 27
15 What is meant by free vortex Understand This would require the CO 5
method? What are the assumptions learner to recall the
used for specific work and constant operation and flow in
axial velocity? axial compressor,
explain the free vortex
method, and
assumptions.
16 Describe about basic operation of Understand This would require the CO 5
axial compressor and illustrate with learner to recall the
a labeled diagram of a compressor axial compressor,
explain the operation
and flow in axial
compressor.
17 Determine the factors affecting stage Understand This would require the CO 5
pressure ratio in a compressor. Is it learner to recall the
important to stage for pressuring operation of
ratio? compressor, interpret
the factors affecting
stage pressure ratio.
18 Explain the velocity diagram of Understand This would require the CO 5
axial and centrifugal compressor learner to recall the
with the help of a neat diagram. operation of
compressor, illustrate
the velocity triangle of
axial and centrifugal
compressor.
19 Explain the performance Understand This would require the CO 5
characteristics of axial and learner to recall the
centrifugal compressor. operation of axial and
centrifugal compressor,
and explain the
performance
characteristics of both
compressors.
20 Describe the methods used to Understand This would require the CO 5
control the surge in compressor. Is learner to recall the
stall and surge same in a concept of surge in
compressor. compressor, explain the
methods to control the
surge, differentiate stall
and surge.
PART C - SHORT ANSWER QUESTIONS
1 What is the function of compressor? Remember — CO 5
2 Compare axial and centrifugal Understand This would require the CO 5
compressor? learner to recall the
function and roles of
compressor, and
compare them based on
nomenclature, and
operation.

Page 28
3 What are the different diffusers used Remember — CO 5
in centrifugal compressor?
4 Define slip factor. Remember — CO 5
5 Define compressor stall Remember — CO 5
6 Define surge. Remember — CO 5
7 Describe about rotating stall. Understand This would require the CO 5
learner to recall the
flow in compressor, and
explain the concept of
rotating stall.
8 Define degree of reaction. Remember — CO 5
9 Explain few stage parameters. Understand This would require the CO 5
learner to recall the
flow in compressor,
explain few stage
parameters like
adiabatic efficiency,
stage loading and flow
coefficients.
10 Define flow coefficient. Remember — CO 5
11 Define stage loading. Remember — CO 5
12 How number of stages calculated in Remember — CO 5
axial flow compressor.
13 Explain isentropic efficiency of a Understand This would require the CO 5
compressor? learner to recall the
performance
parameters of a
compressor, explain the
isentropic efficiency of
a compressor.
14 Define blade efficiency. Remember — CO 5
15 Define stage efficiency for Remember — CO 5
compressor.
16 Describe about compressor cascade. Understand This would require the CO 5
learner to recall the
flow in compressor,
explain compressor
cascade experimental
behavior, and aerofoils.
17 Define polytropic efficiency of a Remember — CO 5
compressor.
18 Explain surge in compressor. Understand This would require the CO 5
learner to recall the
flow in compressor,
explain the surge in
compressor.
19 What is IGV and why is it provided? Remember — CO 5
20 Define hysteresis. Remember — CO 5
MODULE V
TURBINES

Page 29
 PART A-PROBLEM SOLVING AND CRITICAL THINKING QUESTIONS
1 A single stage gas turbine operates Apply This would require the CO 5
at its design condition with an axial learner to recall
absolute flow at entry and exit from governing equations of
the stage. The absolute flow angle turbine, interpret the
at the nozzle exit is 700 . At stage given data, conditions,
entry, the total pressure and and apply them to
temperature are 311 kPa and 8500 C calculate the specific
respectively. The exhaust static work done, M, axial
pressure is 100 kPa, the total to velocity, and stage
static efficiency is 0.87 and mean reaction.
blade speed is 500 m/s. Assuming
constant axial velocity through the
stage, determine (a) the specific
work done (b) the Mach number
leaving the nozzle (c) the axial
velocity (d) total to total efficiency
(e) stage reaction.
2 Combustion gases enter the first Apply This would require the CO 5
stage of a gas turbine at a learner to recall
stagnation temperature and pressure governing equations of
of 1200 K and 4.0 bar. The rotor turbine, interpret the
blade tip diameter is 0.75m, the given data, conditions,
blade height is 0.12 m and the shaft and apply them to
speed is 10,500 rpm. At the mean calculate the flow
radius the stage operates with a angles, velocity, the
reaction of 50%, a flow coefficient of static temperature and
0.7and a stage loading coefficient of pressure at nozzle exit.
2.5. Determine (a) the relative and
absolute flow angles for the stage;
(b) the velocity at nozzle exit; (c)
the static temperature and pressure
at nozzle exit assuming a nozzle
efficiency of 0.96 and the mass flow.
3 A single stage axial flow turbine Apply This would require the CO 5
operates with an inlet temperature learner to recall
of 1100 K and total pressure of 3.4 governing equations of
bar. The total temperature drop turbine, interpret the
across the stage is 144 K and the given data, conditions,
isentropic efficiency of the turbine is and apply them to
0.9. The mean blade speed is 298 calculate the
m/s and the mass flow rate is 18.75 blade-loading
kg/s. The turbine operates with a coefficient, pressure
rotational speed of 12000 rpm. If the ratio of the stage, and
convergent nozzle is operating under the flow angles.
choked condition determine (a)
blade-loading coefficient (b) pressure
ratio of the stage and (c) flow angles.

Page 30
4 A multi-stage axial turbine is to be Apply This would require the CO 5
designed with impulse stages and is learner to recall
to operate with an inlet pressure governing equations of
and temperature of 6 bar and 900 K turbine, interpret the
and outlet pressure of 1 bar. The given data, conditions,
isentropic efficiency of the turbine is and apply them to
85 %. All the stages are to have a estimate the number
nozzle outlet angle of 750 and equal for stages required.
inlet and outlet rotor blade angles.
Mean blade speed is 250 m/s and
the axial velocity is 150 m/s and is
a constant across the turbine.
Estimate the number for stages
required for this turbine.
5 A pulsejet engine is employed in Apply This would require the CO 5
powering a vehicle flying at a Mach learner to recall the
number of 2 at an altitude of 40,000 flight speed expression,
ft. The engine has an inlet area relate the M, inlet area,
0.084 m2 . The pressure ratio at altitude, pressures at
combustion chamber is P03 /P02 = 9, inlets, outlets, and
fuel heating value is 43,000 kJ/kg, solve for air mass flow
and combustion efficiency is 0.96. arte, temperature,
Assuming ideal diffuser (P02 = P0a ), fuel-to-air ratio,
it is required to calculate a). The air exhaust velocity, thrust
mass flow rate, b) The maximum force, and TSFC.
temperature, c) The fuel-to-air ratio,
d) The exhaust velocity, e) The
thrust force, f) The TSFC.
6 A single stage gas turbine operates Apply This would require the CO 5
at its design condition with an axial learner to recall
absolute flow at entry and exit from governing equations of
the stage. The absolute flow angle turbine, interpret the
at the nozzle exit is 700 . At stage given data, conditions,
entry, the total pressure and apply them to calculate
temperature are 311 kPa and 8500 C the specific work done,
respectively. The exhaust static M, axial velocity, total
pressure is 100 kPa, the total to to total efficiency, and
static efficiency is 0.87 and mean stage reaction.
blade speed is 500 m/s. Assuming
constant axial velocity through the
stage, calculate (a) the specific work
done (c) the Mach number leaving
the nozzle (c) the axial velocity (d)
total to total efficiency (e) stage
reaction.

Page 31
7 Combustion gases enter the first Apply This would require the CO 5
stage of a gas turbine at a learner to recall
stagnation temperature and pressure governing equations of
of 1200 K and 4.0 bar. The rotor turbine, interpret the
blade tip diameter is 0.75m, the given data, conditions,
blade height is 0.12 m and the shaft apply them to calculate
speed is 10,500 rpm. At the mean the relative, absolute
radius the stage operates with a flow angles for the
reaction of 50%, a flow coefficient of stage, the velocity at
0.7and a stage loading coefficient of nozzle exit, the static
2.5. Determine (a) the relative and temperature and
absolute flow angles for the stage; pressure at nozzle exit,
(b) the velocity at nozzle exit; (c) and the mass flow.
the static temperature and pressure
at nozzle exit assuming a nozzle
efficiency of 0.96 and the mass flow.
8 A single stage axial flow turbine Apply This would require the CO 5
operates with an inlet temperature learner to recall
of 1100 K and total pressure of 3.4 governing equations of
bar. The total temperature drop turbine, interpret the
across the stage is 144 K and the given data, conditions,
isentropic efficiency of the turbine is apply them to calculate
0.9. The mean blade speed is 298 blade-loading
m/s and the mass flow rate is 18.75 coefficient, pressure
kg/s. The turbine operates with a ratio of the stage, and
rotational speed of 12000 rpm. If the flow angles.
convergent nozzle is operating under
choked condition determine (a)
blade-loading coefficient (b) pressure
ratio of the stage and (c) flow angles.
9 A multi-stage axial turbine is to be Apply This would require the CO 5
designed with impulse stages and is learner to recall
to operate with an inlet pressure governing equations of
and temperature of 6 bar and 900 K turbine, interpret the
and outlet pressure of 1 bar. The given data, conditions,
isentropic efficiency of the turbine is apply them to calculate
85 %. All the stages are to have a the number of stages
nozzle outlet angle of 750 and equal required for the
inlet and outlet rotor blade angles. turbine.
Mean blade speed is 250 m/s and
the axial velocity is 150 m/s and is
a constant across the turbine.
Estimate the number for stages
required for this turbine.
Part - B (Long Answer Questions)
1 Explain the principle of operation of Understand This would require the CO 5
axial flow turbine and polytropic learner to recall the
efficiency of a turbine. operation of turbine,
interpret the principle
of operation of axial
flow turbine, and the
efficiency.

Page 32
2 What do you understand by profile Understand This would require the CO 5
loss? Explain work done and learner to recall the
pressure rise by radial flow turbine. operation of turbine,
interpret the profile
loss, work done, and
pressure rise
3 What are the limitations of axial Understand This would require the CO 5
and radial flow turbine? Clearly learner to recall the
differentiate the two with suitable operation of axial and
justification. radial turbine, compare
them both and their
limitations. .
4 Explain performance characteristics Understand This would require the CO 5
of turbine. Is an axial flow invariably learner to recall the
different from a radial flow? operation of turbine,
interpret the
performance
characteristics, axial
flow, and radial flow in
turbines.
5 Illustrate the velocity diagram for Understand This would require the CO 5
axial flow turbine. Clearly mention learner to recall the
the nomenclature. operation, flow of
turbine, illustrate the
velocity triangle for
axial flow turbine.
6 What do you understand by inlet Understand This would require the CO 5
total pressure? Explain limiting learner to recall the
factors in turbine blade design. operation of turbine,
interpret the inlet total
pressure, and limiting
factors in turbine blade
design.
7 What is the need for turbine blade Understand This would require the CO 5
cooling and explain about different learner to recall the
types of turbine blade cooling operation of turbine,
interpret the need for
cooling and methods.
8 What do you understand by ramjet Understand This would require the CO 5
combustor? Explain about the step learner to recall the
by step procedure to design a ramjet operation of a ramjet,
engine. explain the design
procedure.
9 Explain in brief about the Understand This would require the CO 5
combustion intensity. Write short learner to recall the
notes on flame stability problems in combustion process in
ramjet combustors. ramjet, explain the
combustion intensity,
and flame stability
issues.

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10 What is the difference between axial Understand This would require the CO 5
flow and radial flow turbine? Draw learner to recall the
a neat sketch for both turbines. operation of axial flow
and radial flow turbine,
compare the principle
of operation of both
turbines.
11 What do you understand by annulus Understand This would require the CO 5
loss? Explain the reason for decrease learner to recall the
in total pressure across turbine? operation of turbine,
interpret the annulus
loss, and decrease in
total pressure.
12 What are the flame stability issues Understand This would require the CO 5
in a ramjet combustor? Elucidate on learner to recall the
the issues and explain about the combustion process in
each in brief. ramjet, explain the
flame stability issues.
13 Explain the working principle of the Understand This would require the CO 5
axial turbine with a neat and learner to recall the
labeled sketch. operation of turbine,
interpret the working
principle of the axial
turbine.
14 Define stage efficiency of a turbine. Understand This would require the CO 5
Write the limitations of the radial learner to recall the
flow turbine and compare that with stage efficiency,
an axial turbine. operation of axial and
radial turbines,
compare both turbines.
15 Explain the working principle of the Understand This would require the CO 5
radial turbine with a neat and learner to recall the
labeled sketch. operation of turbine,
interpret the working
principle of the radial
turbine.
16 Explain the working principle of a Understand This would require the CO 5
turbine and a compressor. Elaborate learner to recall the
on the differences between turbine components of
and compressor. compressor and
turbine, compare the
principle of operation
of compressor and
turbine.
17 Compare the closed and open cycle Understand This would require the CO 5
gas turbine. State the advantages of learner to recall the
closed cycle gas turbine over an operation of turbines,
open cycle gas turbine. compare closed and
open cycle gas turbine.

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18 What is the need for turbine blade Understand
This would require the CO5
cooling? Explain about the various learner to recall the
types of cooling methods available operation of turbine,
for turbine blade. interpret need for
turbine blade cooling,
and methods of cooling.
PART C - SHORT ANSWER QUESTIONS
1 What is the function of turbine? Remember — CO 5
2 Compare axial flow and radial flow Understand This would require the CO 5
turbine? learner to recall the
function and roles of
axial flow and radial
flow turbines, compare
them based on
nomenclature, and
operation.
3 Write limitations of radial flow Remember — CO 5
turbine.
4 Compare turbine and compressor. Understand This would require the CO 5
learner to recall the
function and roles of
compressor, turbine,
compare them based on
nomenclature, and
operation.
5 Define stage efficiency of turbine. Remember — CO 5
6 What is the need for turbine blade Remember — CO 5
cooling?
7 Write different types of turbine Remember — CO 5
blade cooling.
8 Describe about profile loss in Understand This would require the CO 5
turbine blade. learner to recall the
flow in turbine, and
explain the profile loss.
9 What is the function of guide vanes Remember — CO 5
in turbine?
10 Define radial flow. Remember — CO 5
11 What is the reason for decrease in Understand This would require the CO 5
total pressure across turbine? learner to recall the
flow in turbine, and
explain the reason for
pressure loss.
12 Define polytropic efficiency of a Remember — CO5
turbine.
13 What do you understand by flame? Remember — CO 5
14 Explain the profile loss? Understand This would require the CO 5
learner to recall the
flow in turbine, and
explain the profile loss.
15 Define annulus loss. Remember — CO 5

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 16 Explain the function of turbine? Understand This would require the CO 5
learner to recall the
flow in turbine, and
explain the operation
of turbine.
17 Define ramjet. Remember — CO 5
18 Explain ramjet combustor? Understand This would require the CO 5
learner to recall the
operation of ramjet and
explain about it.
19 Define axial flow. Remember — CO 5
20 Define vortex. Remember — CO 5

Course Coordinator: HOD AE

Dr. Praveen Kumar Balguri

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