Combustor seal system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10041416-B2
Application number	US-201314430334-A
Country	US
Kind code	B2
Filing date	Sep 30, 2013
Priority date	Sep 29, 2012
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane.

First claim

The invention claimed is:

1. A system for providing a seal between a combustor and a turbine vane, the system comprising:
an airfoil extending between an inner platform and an outer platform of the turbine vane, the outer platform including a platform surface on an axially forward side of the outer platform;
a flange extending radially outward from the combustor, the flange including a flange surface on an axially aft side of the flange, wherein the flange surface is configured to face toward the platform surface of the vane; and
a combustor seal with a body including an axially forward end and an axially aft end, wherein the body includes a radially inward projection adjacent the axially aft end, and
wherein the combustor seal is configured to be axially loaded between the flange surface of the flange and the platform surface of the vane.

2. The system of claim 1 , wherein the flange is integrally formed with the combustor.

3. The system of claim 1 , wherein the combustor seal is held against the flange surface and against the platform surface of the vane solely by an axial load.

4. The system of claim 1 , wherein the combustor seal is a single, ring-shaped piece.

5. The system of claim 1 , wherein the combustor seal includes a plurality of arcuate pieces forming a ring when held against the flange surface of the flange and against the platform surface of the vane by the axial load.

6. The system of claim 1 , wherein the combustor seal is made of a high-temperature alloy based on at least one of nickel and cobalt.

7. The system of claim 1 , wherein the combustor seal includes an upstream surface on the axially forward end of the combustor seal, wherein the upstream surface of the combustor seal abuts the flange surface of the flange.

8. The system of claim 1 , wherein the combustor seal includes a downstream surface on the axially aft end of the combustor seal, wherein the downstream surface of the combustor seal abuts the platform surface of the outer platform.

9. A gas turbine engine comprising:
a combustor including:
a radially extended flange near a downstream end of the combustor, the flange including a flange surface facing in a downstream axial direction;
a turbine vane downstream of the combustor, the turbine vane including an airfoil extending between an inner platform and an outer platform, wherein the outer platform includes a vane surface facing in an upstream axial direction opposite the flange surface; and
a combustor seal with a body including an axially forward end and an axially aft end, wherein the body includes a radially inward projection adjacent the axially aft end, and
wherein the combustor seal is axially loaded against the flange surface of the flange and the vane surface of the outer platform to seal a gap defined between the combustor and the turbine vane.

10. The engine of claim 9 , wherein the engine further comprises:
an outer casing radially outward from the combustor;
an inner casing radially inward from the combustor;
an inner support connecting the combustor to the inner casing; and
an outer support connecting the turbine vane to the outer casing;
wherein elastic deformation of at least one of the inner casing, the inner support, the outer casing, the outer support, the combustor, and the turbine vane provides an axial load on the combustor seal.

11. The engine of claim 10 , wherein the axial load does not exceed the yield strength of the inner casing, the inner support, the outer casing, the outer support, the combustor, and the turbine vane.

12. The engine of claim 9 , wherein the flange extends radially outward from the combustor.

13. The engine of claim 9 , wherein the combustor seal is held against the flange surface and against the vane surface solely by an axial load.

14. The engine of claim 9 , wherein the combustor seal is a single, ring-shaped piece.

15. The engine of claim 9 , wherein the combustor seal includes a plurality of arc-shaped pieces forming a ring extending circumferentially around a center line of the engine when held against the flange surface and against the vane surface by an axial load.

16. The engine of claim 9 , wherein the combustor seal is made of a high-temperature alloy based on at least one of nickel and cobalt.

17. A method of sealing between an annular combustor and a turbine vane, the method comprising:
positioning a combustor seal between a flange surface of the annular combustor and a vane surface of the turbine vane, wherein the combustor seal includes a body with an axially forward end and an axially aft end, and wherein the body includes a radially inward projection adjacent the axially aft end; and
assembling an outer casing radially outward from the annular combustor, an inner casing radially inward from the combustor, an inner support connecting the combustor to the inner casing, and an outer support connecting the turbine vane to the outer casing with the combustor seal to provide axial loading on the combustor seal.

18. The method of claim 17 , wherein the combustor seal is secured against the flange surface and the vane surface solely by axial loading.

Assignees

• United Technologies Corp

Inventors

• Low Kevin Joseph
• Wong Joey

Classifications

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• Y10T29/4932

  Turbomachine making · CPC title

• F05D2240/55

  Seals · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title