US 20130108418A1
(19) United States
(12) Patent Application Publication (10) Pub. No.: US 2013/0108418 A1
Morgan et al.
(54)
(43) Pub. Date:
METALLIC STATOR SEAL
(75) Inventors: Victor J. Morgan, Greenville, SC (US);
Neelesh N. SaraWate, Niskayuna, NY
(US); David W. Weber, Greenville, SC
Publication Classi?cation
(51) Int. Cl.
F01D 11/08
(52) US, CL
(Us)
(73) Assignee: GENERAL ELECTRIC COMPANY,
Schenectady, NY (US)
May 2, 2013
(2006.01)
USPC ..................................................... .. 415/1742
(57)
ABSTRACT
(21)
App1,No,; 13/281,627
The present application provides a seal assembly for a tur
bine. The seal assembly may include a ?rst metal shim, a
(22)
Filed:
second metal shim, and one or more ?exible layers positioned
between the ?rst metal shim and the second metal shim.
Oct. 26, 2011
Patent Application Publication
May 2, 2013 Sheet 1 0f 2
US 2013/0108418 A1
30
16
Fig. 1
E
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Patent Application Publication
110,130
May 2, 2013 Sheet 2 0f 2
129, 140
Fig. 3
US 2013/0108418 A1
May 2,2013
US 2013/0108418 A1
[0001]
METALLIC STATOR SEAL
BRIEF DESCRIPTION OF THE DRAWINGS
TECHNICAL FIELD
[0009] FIG. 1 is a schematic vieW of a gas turbine engine
shoWing a compressor, a combustor, and a turbine.
The present application and the resultant patent
relate generally to gas turbine engines and more particularly
relate to stator seals having a number of metallic layers and
[0010]
FIG. 2 is a partial side vieW ofa turbine.
[0011] FIG. 3 is a side cross-sectional vieW of a stator seal
assembly as may be described herein.
cloth layers for reduced leakage.
DETAILED DESCRIPTION
BACKGROUND OF THE INVENTION
[0002]
Leakage of hot combustion gases and/or cooling
?oWs betWeen turbine components generally causes reduced
poWer output and loWer e?iciency. For example, the hot com
bustion gases may be contained Within the turbine by provid
ing pressuriZed compressor air around the hot gas path. Leak
age of high pressure cooling ?oWs into the hot gas path thus
may lead to detrimental parasitic losses. Overall e?iciency
thus may be improved by blocking the leakage locations
While providing cooling ?oW only as required.
[0003]
For example, current gas turbines may use cloth
seals betWeen adjacent stator components to limit the leakage
of cooling ?oWs therebetWeen. Such cloth seals may have a
Woven Wire mesh cloth layer Wrapped around a metal shim
With a curved shepherds hook on either side. Manufactur
ing variations, hoWever, involved in creating the shepherds
[0012] Referring noW to the draWings, in Which like numer
als refer to like elements throughout the several vieWs, FIG. 1
shoWs a schematic vieW of gas turbine engine 10 as may be
used herein. The gas turbine engine 10 may include a com
pressor 15. The compressor 15 compresses an incoming How
of air 20. The compressor 15 delivers the compressed How of
air 20 to a combustor 25. The combustor 25 mixes the com
pressed ?oW of air 20 With a pressuriZed How of fuel 30 and
ignites the mixture to create a How of combustion gases 35.
Although only a single combustor 25 is shoWn, the gas turbine
engine 10 may include any number of combustors 25. The
How of combustion gases 35 is in turn delivered to a turbine
40. The How of combustion gases 35 drives the turbine 40 so
as to produce mechanical Work. The mechanical Work pro
duced in the turbine 40 drives the compressor 15 via a shaft 45
and an external load 50 such as an electrical generator and the
date, hoWever, the use of such thin metal shims in heavy duty
like.
[0013] The gas turbine engine 10 may use natural gas,
various types of syngas, and/or other types of fuels. The gas
turbine engine 10 may be any one of a number of different gas
gas turbines has not been feasible given concerns With robust
turbine engines offered by General Electric Company of
ness as Well as manufacture and assembly issues With such
Schenectady, NY. including, but not limited to, those such as
a 7 or a 9 series heavy duty gas turbine engine and the like.
hook and the overall cloth seal may impact the leakage rate
therethrough. Even loWer leakage rates may be achieved by
using thin metal shims betWeen the stator components. To
seals.
[0004]
There is thus a desire for an improved seal assembly
The gas turbine engine 10 may have different con?gurations
for use betWeen stator components and other components in a
and may use other types of components. Other types of gas
heavy duty gas turbine engine. Such a seal assembly may be
substantially temperature resistant, Wear resistant, and ?ex
turbine engines also may be used herein. Multiple gas turbine
engines, other types of turbines, and other types of poWer
ible so as to provide adequate sealing With a robust compo
generation equipment also may be used herein together.
nent lifetime.
more ?exible layers positioned betWeen the ?rst metal shim
and the second metal shim.
[0014] FIG. 2 shoWs a portion of an example of the turbine
40. Generally described, the turbine 40 may include a ?rst
stage noZZle 55 and a ?rst stage bucket 60 in a ?rst stage 65.
Also shoWn is a second stage noZZle 70 of a second stage 75.
Any number of stages may be used herein. The second stage
noZZle 70 may be positioned about a diaphragm 80. The
noZZle 70 and the diaphragm 80 form part of a stator 85. Any
number of stators 85 may be positioned circumferentially
about an axis 90 in each of the stages. A stator seal 95 may be
[0006]
positioned betWeen adjacent stators 85 about the diaphragm
SUMMARY OF THE INVENTION
[0005]
The present application and the resultant patent thus
provide a seal assembly for a turbine. The seal assembly may
include a ?rst metal shim, a second metal shim, and one or
The present application and the resultant patent fur
ther may provide a turbine. The turbine may include a ?rst
80 or elseWhere. The stator seals 95 prevent the leakage of the
stator, a second stator, and a seal assembly positioned
cooling air ?oWs 20 from the compressor therethrough. Other
components and other con?gurations may be used herein. For
betWeen the ?rst stator and the second stator. The seal assem
bly may include a pair of metal shims surrounding one or
more cloth layers.
[0007]
The present application and the resultant patent fur
ther may provide a turbine. The turbine may include a ?rst
stator, a second stator, and a seal assembly positioned
betWeen the ?rst stator and the second stator. The seal assem
bly may include a ?rst metal shim in a top position, a second
metal shim in a bottom position, and a ?rst Woven Wire mesh
and a second Woven Wire mesh in a middle position.
[0008] These and other features and improvements of the
present application and the resultant patent Will become
apparent to one of ordinary skill in the art upon revieW of the
folloWing detailed description When taken in conjunction
With the several draWings and the appended claims.
example, other components may include shrouds, casings,
noZZles, transition pieces, and the like.
[0015]
FIG. 3 shoWs portions of an example of a turbine
100 as may be described. herein. Speci?cally, a ?rst turbine
component 110 and a second turbine component 120 are
shoWn. The turbine components 110, 120 may be a ?rst
noZZle 130 of a ?rst stator 135 and a second noZZle 140 of a
second stator 150 as described above or any other pair of
adjacent turbine components. Any number or type of turbine
components may be used herein.
[0016] The turbine 100 may include a seal assembly 160
positioned betWeen each pair of the turbine components 110,
120. The seal assembly 160 may extend from a ?rst seal slot
170 in the ?rst turbine component 110 to a second seal slot
May 2,2013
US 2013/0108418 A1
180 in the second turbine component 120. The seal slots 170,
180 may have any size, shape, or con?guration. The seal
assembly 160 blocks a gap 190 between the components 110,
We claim:
1. A seal assembly for a turbine, comprising:
The metal shims 200, 210 may be relatively thin but solid
a ?rst metal shim;
a second metal shim; and
one or more ?exible layers positioned betWeen the ?rst
metal shim and the second metal shim.
2. The seal assembly of claim 1, Wherein the one or more
?exible layer comprise one or more cloth layers.
3. The seal assembly of claim 2, Wherein the one or more
metal stock. The metal shims 200, 210 may be made out of a
high temperature resistant material such as stainless steel or a
layer.
120 so as to prevent the escape of the cooling air ?oWs 20
therethrough and the like. Other locations may be used herein.
[0017]
The seal assembly 160 may include a pair of metal
shims: a ?rst metal shim 200 and a second metal shim 210.
nickel based alloy Other types of materials may be used
herein. Additional metal shim layers also may be used.
[0018] The seal assembly 160 also may include a pair of
?exible cloth layers: a ?rst cloth layer 220 and a second cloth
layer 230. Any number of the ?exible cloth layers 220, 230
may be used herein. The ?exible cloth layers 220, 230 may be
made out of a Woven Wire mesh 240 or any ?exible high
temperature material. For example, metal foam, a holloW
box-type shim, or even additional Welded shim layers and the
like may be used. The ?rst metal shim 200 may have a top
position 250, the second metal shim 210 may have a bottom
position 260, and the ?exible cloth layers 220, 230 may have
a middle position 270. (The terms top, bottom, middle,
re?ect relative, as opposed to absolute, positions.) The metal
shims 200, 210 and the ?exible cloth layers 220, 230 may be
coupled via high temperature adhesives, high strength fasten
ers, Welding, and other types of conventional fastening
means. The seal assembly 160 and the components thereof
may have any desired siZe, shape, or con?guration. Addi
cloth layers comprise a ?rst cloth layer and a second cloth
4. The seal assembly of claim 2, Wherein the one or more
cloth layers comprise a Woven Wire mesh.
5. The seal assembly of claim 1, Wherein the ?rst metal
shim comprises a top position.
6. The seal assembly of claim 1, Wherein the second metal
shim comprises a bottom position.
7. The seal assembly of claim 1, Wherein the one or more
?exible layers comprise a middle position.
8. The seal assembly of claim 1, Wherein the ?rst metal
shim and the second metal shim comprise a temperature
resistant material.
9. The seal assembly of claim 1, Wherein either the ?rst
metal shim or the second metal shim comprises a sealing
surface facing a gap betWeen a ?rst seal slot and a second seal
slot.
10. The seal assembly of claim 9, Wherein the ?rst seal slot
is positioned Within a ?rst turbine component and the second
seal slot is positioned Within a second turbine component.
11. The seal assembly of claim 10, Wherein the ?rst turbine
component comprises a ?rst stator and the second turbine
component comprises a second stator.
12. A turbine, comprising:
add thickness therein Without impacting on overall ?exibility.
a ?rst stator;
a second stator; and
[0019] The use of the metal shims 200, 210 in both the top
position 250 and the bottom position 260 thus alloWs the seal
a seal assembly positioned betWeen the ?rst stator and the
second stator;
the seal assembly comprising a pair of metal shims sur
tional non-metallic ?ller materials also may be used so as to
assembly 160 to be reversible, i.e., the seal assembly 160 may
be installed With either position on the load surface in the seal
slots 170, 180 of the turbine components 110, 120. The metal
shim layers 200, 210 act as the seal surface so as to provide
loW leakage rates therethrough. The metal shim 200 in the top
rounding one or more cloth layers.
13. The turbine of claim 12, Wherein the pair of metal shims
comprises a ?rst metal shim in a top position and a second
metal shim in a bottom position.
14. The turbine of claim 12, Wherein the one or more cloth
position 250 also serves as a supplemental leakage barrier in
the event that the metal shim 210 in the bottom position 260
layers comprise a ?rst cloth layer and a second cloth layer.
is somehoW compromised. The ?exible cloth layers 220, 230
provide thickness to the seal assembly 160 Without substan
tially increasing overall stiffness. The ?exible cloth layers
220, 230 also mitigate potential assembly or maintenance
layers comprise a Woven Wire mesh.
concerns.
[0020]
The seal assembly 160 thus provides loW leakage
rate similar to that possible With thin metal shim seals While
eliminating the manufacturing, assembly, and robustness
concerns When applied to a heavy duty gas turbine. Moreover,
the seal assembly 160 may be less susceptible to manufactur
ing, variations as compared to existing cloth seals. The seal
15. The turbine of claim 12, Wherein the one or more cloth
16. The turbine of claim 12, Wherein the one or more cloth
layers comprise a middle position.
17. The turbine of claim 12, Wherein the pair of metal shims
comprises a temperature resistant material.
18. The turbine of claim 12, Wherein the ?rst stator com
prises a ?rst seal slot and the second stator comprises a second
seal slot.
19. The turbine of claim 18, Wherein one of the pair of
metal shims comprises a sealing surface facing a gap betWeen
the ?rst seal slot and the second seal slot.
20. A turbine, comprising:
assembly 160 thus reduces leakage With loW manufacturing
and operational risks. The seal assembly 160 may be original
a ?rst stator;
a second stator; and
equipment or part of a retro?t.
a seal assembly positioned betWeen the ?rst stator and the
second stator;
the seal assembly comprising a ?rst metal shim in a top
position, a second metal shim in a bottom position, and
[0021]
It should be apparent that the foregoing relates only
to certain embodiments of the present application and the
resultant patent. Numerous changes and modi?cations may
be made herein by one of ordinary skill in the art Without
departing from the general spirit and scope of the invention as
de?ned by the folloWing claims and the equivalents thereof.
a ?rst Woven Wire mesh and a second Woven Wire mesh
in a middle position.
*
