Cooled combustor for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017191664-A1
Application number	US-201614988068-A
Country	US
Kind code	A1
Filing date	Jan 5, 2016
Priority date	Jan 5, 2016
Publication date	Jul 6, 2017
Grant date	—

Abstract

A combustor for a gas turbine engine comprises a liner having a forward opening and an aft opening. A deflector closes the forward opening and the aft opening is in fluid communication with a turbine section downstream of the combustor. A dome disposed in the deflector provides a fuel/air mixture to be ignited to drive the turbine section. A gap can be disposed between the deflector and the liner, having film holes disposed in the deflector for providing a flow of cool air to the gap for cooling the combustion liner downstream of the gap.

First claim

What is claimed is:

1 . A method of cooling a combustor for a gas turbine engine, the method comprising:
supplying an impinging airflow onto a deflector of the combustor; and after impingement onto the deflector, supplying the impinging airflow through film holes in the combustor to define a film of cooling air along at least a portion of a liner.

2 . The method of claim 1 wherein the supplying an impinging airflow comprises supplying cooling air through an impingement baffle spaced from the deflector.

3 . The method of claim 2 wherein the supplying an impinging airflow comprises supplying compressor air from a compressor section of the gas turbine engine.

4 . The method of claim 2 wherein supplying the impinging airflow through the film holes comprises supplying impinging airflow through film holes passing through at least one of the deflector and liner.

5 . The method of claim 4 wherein the film holes pass through both the deflector and liner.

6 . The method of claim 1 wherein the film of cooling air flows along an interior of the liner.

7 . A combustor for a gas turbine engine comprising:
a liner defining a forward opening and an aft opening; a deflector closing the forward opening; a dome located in the deflector; and film holes extending through the combustor from the deflector to an interior of the liner.

8 . The combustor of claim 7 wherein the film holes extend through at least one of the deflector and the liner.

9 . The combustor of claim 8 wherein the film holes extend through both the deflector and liner.

10 . The combustor of claim 8 further comprising an impingement baffle upstream of the deflector.

11 . The combustor of claim 10 wherein the impingement baffle and deflector at least partially define an impingement chamber and the film holes are fluidly coupled to the impingement chamber.

12 . The combustor of claim 11 wherein the deflector terminates prior to the liner to define a gap and the film holes are fluidly coupled to the gap.

13 . The combustor of claim 7 further comprising an impingement baffle upstream of the deflector.

14 . The combustor of claim 13 wherein the impingement baffle and deflector at least partially define an impingement chamber and the film holes are fluidly coupled to the impingement chamber.

15 . The combustor of claim 7 wherein the deflector terminates prior to the liner to define a gap and the film holes are fluidly coupled to the gap.

16 . A combustor for a gas turbine engine comprising a deflector, a liner spaced from the deflector and defining a gap there between, and at least one film hole extending through the deflector and having an outlet opening into the gap.

17 . The combustor of claim 16 further comprising an impingement baffle upstream of the deflector.

18 . The combustor of claim 17 wherein the impingement baffle and deflector at least partially define an impingement chamber and the at least one film hole has an inlet fluidly coupled to the impingement chamber.

19 . The combustor of claim 16 wherein the at least one film hole extends through at least one of the deflector and the liner.

20 . The combustor of claim 16 wherein the at least one film hole extend primarily radially through the deflector.

Assignees

• Gen Electric

Inventors

• Bennett William Thomas

Classifications

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23R3/42

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title