Combustor Assembly

Patent metadata

Field	Value
Publication number	US-2017248317-A1
Application number	US-201615053582-A
Country	US
Kind code	A1
Filing date	Feb 25, 2016
Priority date	Feb 25, 2016
Publication date	Aug 31, 2017
Grant date	—

Abstract

A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.

First claim

What is claimed is:

1 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:
an inner liner, an outer liner, and a combustor dome together defining at least in part a combustion chamber having an annulus height, the combustor dome additionally defining an opening; and a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield located at least partially within the combustion chamber for shielding at least a portion of the fuel-air injector hardware assembly, the heat shield defining an outer diameter, a ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield being at least about 1.3:1.

2 . The combustor assembly of claim 1 , wherein the ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield is at least about 1.5:1.

3 . The combustor assembly of claim 1 , wherein the combustor dome further comprises a plurality of openings, wherein the combustor dome defines a spacing from a center of one opening to a center of an adjacent opening, and wherein a ratio of the spacing to the outer diameter of the heat shield is at least about 1.3:1.

4 . The combustor assembly of claim 1 , wherein the combustor dome is formed of a ceramic matrix composite material.

5 . The combustor assembly of claim 1 , wherein the heat shield comprises a metal material.

6 . The combustor assembly of claim 1 , wherein the heat shield comprises a heat deflector lip, wherein the heat deflector lip of the heat shield defines a circular shape, and wherein the heat deflector lip defines the outer diameter.

7 . The combustor assembly of claim 1 , wherein the combustor assembly defines a centerline, wherein the combustor dome comprises a forward wall, wherein the forward wall of the combustor dome defines a direction intersecting the centerline, and wherein the annulus height is defined in a direction parallel to the direction of the forward wall of the combustor dome.

8 . The combustor assembly of claim 1 , wherein the annulus height is defined between the inner liner and the outer liner.

9 . The combustor assembly of claim 1 , wherein fuel-air injector hardware assembly further comprises a swirler and a seal plate, wherein the swirler and seal plate define a maximum outer diameter, wherein the outer diameter of the heat shield is greater than the maximum outer diameter of the swirler and seal plate.

10 . The combustor assembly of claim 1 , wherein the combustor assembly defines a centerline, wherein the combustor dome comprises a forward wall, wherein the forward wall of the combustor dome defines a direction intersecting the centerline, wherein the forward wall further defines a length in the direction of the forward wall, and wherein a ratio of the length of the forward wall to the outer diameter of the heat shield is at least about 1.1:1.

11 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:
an inner liner, an outer liner, and a combustor dome together defining at least in part a combustion chamber, the combustor dome additionally defining a plurality of openings and a spacing, each opening having a center, and the spacing being defined from a center of one opening to a center of an adjacent opening; and a plurality of fuel-air injector hardware assemblies, each fuel-air injector hardware assembly positioned at least partially within a respective one of the plurality of openings of the combustor dome and comprising a heat shield, the heat shield located at least partially within the combustion chamber for shielding at least a portion of the fuel-air injector hardware assembly, each heat shield defining an outer diameter, a ratio of the spacing to the outer diameter of the heat shield being at least about 1.3:1.

12 . The combustor assembly of claim 11 , wherein a ratio of the spacing to the outer diameter of the heat shield is at least about 1.5:1.

13 . The combustor assembly of claim 11 , wherein the combustion chamber defines an annulus height, and wherein a ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield is at least about 1.3:1.

14 . The combustor assembly of claim 13 , wherein the combustor assembly defines a centerline, wherein the combustor dome comprises a forward wall, wherein the forward wall of the combustor dome defines a direction intersecting the centerline, and wherein the annulus height is defined in a direction parallel to the direction of the forward wall of the combustor dome.

15 . The combustor assembly of claim 13 , wherein the annulus height is defined between the inner liner and the outer liner.

16 . The combustor assembly of claim 11 , wherein the combustor dome is formed of a ceramic matrix composite material.

17 . The combustor assembly of claim 11 , wherein the heat shield comprises a metal material.

18 . The combustor assembly of claim 17 , wherein the heat shield further comprises an environmental barrier coating.

19 . The combustor assembly of claim 11 , wherein the heat shield comprises a heat deflector lip, and wherein the heat deflector lip of the heat shield defines a circular shape.

20 . The combustor assembly of claim 11 , wherein fuel-air injector hardware assembly further comprises a swirler and a seal plate, wherein the swirler and seal plate define a maximum outer diameter, wherein the outer diameter of the heat shield is greater than the maximum outer diameter of the swirler and seal plate.

Assignees

• Gen Electric

Inventors

• Hannwacker David Andrew
• Howell Stephen John
• Jacobson John Carl
• Monty Joseph Douglas

Classifications

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/38 Primary

  comprising rotary fuel injection means · CPC title

• F23R3/14

  by using swirl vanes · CPC title