U.S. patent application number 13/633890 was filed with the patent office on 2014-04-03 for solid seal with cooling pathways.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is GENERAL ELECTRIC COMPANY. Invention is credited to Randall Richard Good, Ibrahim Sezer.
Application Number | 20140093353 13/633890 |
Document ID | / |
Family ID | 49322199 |
Filed Date | 2014-04-03 |
United States Patent
Application |
20140093353 |
Kind Code |
A1 |
Sezer; Ibrahim ; et
al. |
April 3, 2014 |
SOLID SEAL WITH COOLING PATHWAYS
Abstract
The present application provides a seal for use between
components facing a high pressure cooling air flow and a hot gas
path in a gas turbine engine. The seal may include a first surface
facing the high pressure cooling air flow, a second surface with a
second surface air plenum facing the hot gas path, and a number of
cooling pathways extending from the first surface to the second
surface air plenum of the second surface for the high pressure
cooling air flow to pass therethrough.
Inventors: |
Sezer; Ibrahim; (Greenville,
SC) ; Good; Randall Richard; (Simpsonville,
SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
GENERAL ELECTRIC COMPANY |
Schenectady |
NY |
US |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
49322199 |
Appl. No.: |
13/633890 |
Filed: |
October 3, 2012 |
Current U.S.
Class: |
415/1 ; 277/628;
277/644 |
Current CPC
Class: |
F01D 11/008 20130101;
F01D 11/005 20130101; F01D 11/006 20130101; F05D 2260/20 20130101;
F01D 11/003 20130101; F01D 25/12 20130101 |
Class at
Publication: |
415/1 ; 277/628;
277/644 |
International
Class: |
F01D 11/00 20060101
F01D011/00; F01D 25/12 20060101 F01D025/12 |
Claims
1. A seal for use between components facing a high pressure cooling
air flow and a hot gas path in a gas turbine engine, comprising: a
first surface facing the high pressure cooling air flow; a second
surface facing the hot gas path; the second surface comprising a
second surface air plenum; and a plurality of cooling pathways
extending from the first surface to the second surface air plenum
of the second surface for the high pressure cooling air flow to
pass therethrough.
2. The seal of claim 1, wherein the seal comprises a solid
seal.
3. The seal of claim 1, wherein the seal comprises a substantial
"I" beam-like shape.
4. The seal of claim 1, wherein the second surface comprises a
second surface peripheral lip.
5. The seal of claim 1, wherein the first surface comprises a first
surface air plenum.
6. The seal of claim 1, wherein the first surface comprises a first
surface peripheral lip.
7. The seal of claim 1, wherein the first surface comprises a top
surface and wherein the second surface comprises a bottom
surface.
8. The seal of claim 1, further comprising a first blocked end and
a second blocked end.
9. The seal of claim 1, wherein the plurality of cooling holes
comprises a straight configuration.
10. The seal of claim 1, wherein the plurality of cooling holes
comprises an angled configuration.
11. The seal of claim 1, wherein the plurality of cooling holes
comprises a plurality of impingement holes.
12. The seal of claim 1, wherein the components comprise a first
stator and a second stator
13. The seal of claim 1, wherein the components define a seal slot
and wherein the seal slot is cooled via the high pressure cooling
air flow from the plurality of cooling pathways.
14. A method of cooling a seal positioned between components in a
gas turbine engine, comprising: flowing high pressure cooling air
about a first surface of the seal; drawing the high pressure
cooling air through a plurality of cooling pathways in the seal;
and drawing the high pressure cooling air through an air plenum
about a second surface of the seal towards a hot gas path.
15. The method of claim 14, further comprising the step of cooling
the components with the high pressure cooling air leaving the air
plenum.
16. A solid seal for use between components facing a high pressure
cooling air flow and a hot gas path in a gas turbine engine,
comprising: a first surface facing the high pressure cooling air
flow; the first surface comprising a first surface air plenum; a
second surface facing the hot gas path; the second surface
comprising a second surface air plenum; and a plurality of cooling
pathways extending from the first surface air plenum of the first
surface to the second surface air plenum of the second surface for
the high pressure cooling air flow to pass therethrough.
17. The solid seal of claim 16, wherein the seal comprises a
substantial "I" beam-like shape.
18. The solid seal of claim 16, wherein the first surface comprises
a first surface peripheral lip and wherein the second surface
comprises a second surface peripheral lip.
19. The solid seal of claim 16, further comprising a first blocked
end and a second blocked end.
20. The solid seal of claim 16, wherein the plurality of cooling
holes comprises a plurality of impingement holes with a straight
configuration and/or an angled configuration.
Description
TECHNICAL FIELD
[0001] The present application and resultant patent relate
generally to gas turbine engines and more particularly relate to
solid seals and the like having cooling pathways extending
therethrough.
BACKGROUND OF THE INVENTION
[0002] Generally described, turbo-machinery such as gas turbine
engines and the like include a main gas flow path extending
therethrough. Gas leakage, either out of the gas flow path or into
the gas flow path, may lower overall gas turbine efficiency,
increase fuel costs, and possibly increase emission levels.
Secondary flows also may be used within the gas turbine engine to
cool the various heated components. Specifically, cooling air may
be extracted from the later stages of the compressor for use in
cooling the heated components and for purging gaps and cavities
between adjacent components. For example, seals may be placed
between turbine components such as stators and the like. These
locations, however, may face very high temperatures and velocities
that may lead to heavy oxidation and even seal failure. This
potential damage may be mitigated somewhat by providing purge air
to the gap with the seal therein. This purge air, however, may be a
largely inefficient use of the cooling air.
[0003] There is thus a desire for improved solid seal for use
between stator components and other components in a heavy duty gas
turbine engine. Such a solid seal may be cooled with less flow than
is generally necessary to purge the gap therein for higher overall
efficiency and with increased component lifetime.
SUMMARY OF THE INVENTION
[0004] The present application and the resultant patent thus
provide a seal for use between components facing a high pressure
cooling air flow and a hot gas path in a gas turbine engine and the
like. The seal may include a first surface facing the high pressure
cooling air flow, a second surface having a second surface air
plenum facing the hot gas path, and a number of cooling pathways
extending from the first surface to the second surface air plenum
of the second surface for the high pressure cooling air flow to
pass therethrough.
[0005] The present application and the resultant patent further
provide a method of cooling a seal positioned between components in
a gas turbine engine. The method may include the steps of flowing
high pressure cooling air about a first surface of the seal,
drawing the high pressure cooling air through a number of cooling
pathways in the seal, and drawing the high pressure cooling air
through an air plenum about a second surface of the seal towards a
hot gas path. The method may include the further step of cooling
the components with the high pressure cooling air passing through
the air plenum.
[0006] The present application and the resultant patent further
provide a solid seal for use between components facing a high
pressure cooling air flow and a hot gas path in a gas turbine
engine. The solid seal may include a first surface with a first
surface air plenum facing the high pressure cooling air flow, a
second surface with a second surface air plenum facing the hot gas
path, and a number of cooling pathways extending from the first
surface air plenum of the first surface to the second surface air
plenum of the second surface for the high pressure cooling air flow
to pass therethrough.
[0007] 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.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a schematic view of a gas turbine engine showing a
compressor, a combustor, and a turbine.
[0009] FIG. 2 is a partial side view of a turbine showing a number
of components positioned along a hot gas path.
[0010] FIG. 3 is a side cross-sectional view of a known seal
positioned between adjacent turbine components.
[0011] FIG. 4 is a perspective view of a solid seal as may be
described herein with a number of cooling pathways extending
therethrough.
[0012] FIG. 5 is a side cross-sectional view of the solid seal of
FIG. 4 with the cooling pathways extending therethrough.
DETAILED DESCRIPTION
[0013] Referring now to the drawings, in which like numerals 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 compressor 15. The compressor
15 compresses an incoming flow of air 20. The compressor 15
delivers the compressed flow of air 20 to a combustor 25. The
combustor 25 mixes the compressed flow of air 20 with a pressurized
flow of fuel 30 and ignites the mixture to create a flow 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 flow of combustion gases 35 is in turn delivered to a turbine
40. The flow of combustion gases 35 drives the turbine 40 so as to
produce mechanical work. The mechanical work produced in the
turbine 40 drives the compressor 15 via a shaft 45 and an external
load 50 such as an electrical generator and the like.
[0014] 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 turbine engines offered
by General Electric Company of Schenectady, New York, including,
but not limited to, those such as a 7 or a 9 series heavy duty gas
turbine engine and the like. The gas turbine engine 10 may have
different configurations and may use other types of components.
Other types of gas turbine engines also may be used herein.
Multiple gas turbine engines, other types of turbines, and other
types of power generation equipment also may be used herein
together.
[0015] FIG. 2 shows a portion of the turbine 40. Generally
described, the turbine 40 may include a first stage nozzle 55, a
first stage bucket 60, and a first stage shroud 62 of a first stage
65. Also shown is a second stage nozzle 70 of a second stage 75.
Any number of stages may be used herein. The nozzles 55, 70 may be
positioned on a diaphragm 80. Any number of nozzles 70 and
diaphragms 80 may be positioned circumferentially about an axis 85.
A seal 90 may be positioned between each pair of adjacent shrouds
62, diaphragms 80, or other turbine components. The seal 90 may be
used between adjacent turbine components so as to prevent the
leakage of the cooling air flows 20 from the compressor 15 or
elsewhere therethrough. As described above, the seals 90 may have
many different configurations. Other types of sealing mechanisms
also may be used. Other components and other configurations may be
used herein.
[0016] FIG. 3 shows an example of the seal 90 positioned between
adjacent turbine components, a first component 92 and a second
component 94. The components 92, 94 may be adjacent turbine
components such as stator components and the like. The turbine
components 92, 94 may define a seal slot 95 therebetween. The seal
90 may be a solid material seal although other types of seals may
be used. Any number of the seals 90 may be used herein. The seals
90 may prevent or reduce leakage of a flow of high pressure cooling
air 96 between the components 92, 94 into the lower pressure hot
gas path 98.
[0017] FIG. 4 shows an example of a seal 100 as may be described
herein. The seal 100 may have a top surface 110, a bottom surface
120 (a slash face), a first side 130, an opposed second side 140, a
first end 150, and an opposed second end 160. (The terms "bottom,"
"top," "side," "end," "first," "second," and the like are used for
the purposes of relative orientation only and not as an absolute
position.) The seal 100 may be a solid seal 170. Alternatively, the
seal 100 may have a number of layers of material therein. The seal
100 may be made out of a high temperature material such as
stainless steel, nickel-based alloys, and the like. Other types of
materials also may be used herein. The seal 100 may have any size,
shape, or configuration.
[0018] As is shown in cross-section in FIG. 5, the seal 100 may
have a substantial "I-beam" like shape 180. Specifically, the seal
100 may include a first plenum 190 defined by a first peripheral
lip 200 about the top surface 110 thereof and a second plenum 210
defined by a second peripheral lip 220 about the bottom surface 120
thereof. The plenums 190, 210 thus may be recessed areas within the
top surface 110 and the bottom surface 120 of the seal. The plenums
190, 210 and the peripheral lips 200, 220 may have any size, shape,
or configuration. Multiple plenums 190, 210 also may be used. The
peripheral lips 200, 220 may define a first blocked end 230 on the
first end 150 and a second blocked end 240 on the second end 160.
The blocked ends 220, 240 may have any size, shape, or
configuration. One or more open ends also may be used.
Alternatively, the blocked ends 220, 240 may have cooling holes or
slots positioned therein. Other components and other configurations
may be used herein.
[0019] The seal 100 also may include a number of cooling pathways
250 extending therethrough from the first plenum 190 to the second
plenum 210. Any number of the cooling pathways 250 may be used
herein. The cooling pathways 250 may have any suitable size, shape,
or configuration. Further, the cooling pathways 250 may extend
through the seal 100 at a straight and/or an angled configuration.
Any angle or combinations of angles may be used. The cooling
pathways 250 may be formed by drilling or other types of
manufacturing techniques. Cooling pathways 250 of differing
configurations may be used herein together. Other components and
other configurations may be used herein.
[0020] In use, the seal 100 may be positioned between the first
component 92 and the second component 94 within the seal slot 95.
The top surface 110 of the seal 100 may face the high pressure
cooling air 96 while the bottom surface 120 may face the lower
pressure hot gas path 98. The seal 100 may have any number of the
cooling pathways 250 extending therethrough in any configuration.
The seal cooling pathways 250 extending into the second plenum 210
also act as impingement holes and/or purge holes for the seal slot
95. Specifically, the pressure differential between the high
pressure cooling air 96 and the lower pressure hot gas path 98
draws the high pressure cooling air 96 through the cooling pathways
250 and into the second plenum 210 about the bottom surface 120 of
the seal 100. The high pressure cooling air 96 thus enhances heat
transfer through the seal 100 and impinges upon/purges the seal
slot 95 via the impingement holes.
[0021] The cooling pathways 250 may be positioned strategically
near localized hot spots or uniformly along the length of the seal
100. The cooling pathways 250 may have any prescribed pitch along
the length of the seal 100. The use of the blocked ends 230, 240
also substantially limits any gap leakage about the ends 150, 160
of the seal 100. The seal 100 and the cooling pathways 250
therethrough thus provide purging and cooling of the bottom surface
120 or the slash face as well as about the sealing slot 95 in an
efficient manner.
[0022] Moreover, the seal 100 described herein may provide
increased seal lifetime, reduced secondary flows, higher overall
engine efficiency, and a reduced heat rate. The seal 100 may be
original equipment or part of a retro-fit. Different configurations
of the seals 100 may be used together herein. The seal 100 also may
be applicable for use in other types of sealing locations.
Specifically, the seal 100 may be used between any two components
with a pressure differential therebetween for a flow of cooling
air.
[0023] It should be apparent that the foregoing relates only to
certain embodiments of the present application and the resultant
patent. Numerous changes and modifications may be made herein by
one of ordinary skill in the art without departing from the general
spirit and scope of the invention as defined by the following
claims and the equivalents thereof.
* * * * *