SOLID SEAL WITH COOLING PATHWAYS
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.
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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 INVENTIONGenerally 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.
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 INVENTIONThe 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.
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.
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.
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.
Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
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.
As is shown in cross-section in
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.
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.
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.
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.
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.
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.
Type: Application
Filed: Oct 3, 2012
Publication Date: Apr 3, 2014
Applicant: GENERAL ELECTRIC COMPANY (Schenectady, NY)
Inventors: Ibrahim Sezer (Greenville, SC), Randall Richard Good (Simpsonville, SC)
Application Number: 13/633,890
International Classification: F01D 11/00 (20060101); F01D 25/12 (20060101);