Combustor assembly

Patent metadata

Field	Value
Publication number	US-10428736-B2
Application number	US-201615053541-A
Country	US
Kind code	B2
Filing date	Feb 25, 2016
Priority date	Feb 25, 2016
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

A combustor assembly for a gas turbine engine includes a combustor dome defining an opening, a cooling hole, and at least in part defining a combustion chamber. The combustor dome includes a first side and a second side, the cooling hole extending from the first side to the second side. The combustor assembly additionally includes a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and including a heat shield. The heat shield includes a heat deflector lip. The cooling hole in the combustor dome is oriented to direct a cooling airflow onto the heat deflector lip to maintain at least a portion of the heat shield within a desired operating temperature range.

First claim

What is claimed is:

1. A combustor assembly for a gas turbine engine, the combustor assembly comprising:
a combustor dome defining an opening and a cooling hole, and at least partially defining a combustion chamber, the combustor dome comprising a first side and a second side, the cooling hole extending from the first side to the second side; and
a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield, the heat shield comprising a heat deflector lip, and the cooling hole in the combustor dome oriented to direct a cooling airflow onto the heat deflector lip, wherein the fuel-air injector hardware assembly defines a centerline;
wherein the heat shield further comprises a flange, wherein a surface of the flange and the heat deflector lip of the heat shield define a channel therebetween configured to receive a cooling airflow from the cooling hole, wherein the cooling hole is oriented to direct the cooling airflow into the channel,
wherein the cooling hole includes an inlet at the first side of the combustor dome and an outlet at the second side of the combustor dome, wherein the heat deflector lip defines an outer tip, and wherein the inlet is positioned a first distance from the centerline and the outer tip of the heat deflector lip is positioned a second distance from the centerline of the fuel-air injector hardware assembly,
wherein the first distance is greater than the second distance; and
wherein the surface of the flange is flush with the second side of the combustor dome.

2. The combustor assembly of claim 1 , wherein the cooling hole slants towards the opening in the combustor dome from the first side of the combustor dome to the second side of the combustor dome.

3. The combustor assembly of claim 1 , wherein the cooling hole is a first cooling hole of a plurality of cooling holes extending from the first side of the combustor dome to the second side of the combustor dome oriented to direct a cooling airflow onto the heat deflector lip.

4. The combustor assembly of claim 3 , wherein the combustor dome defines a circumference extending around the opening, and wherein the plurality of cooling holes are spaced along the circumference extending around the opening.

5. The combustor assembly of claim 1 , wherein the heat deflector lip comprises a hot side and a cold side, and wherein the cooling hole in the combustor dome is oriented to direct the cooling airflow onto the cold side of the heat deflector lip.

6. The combustor assembly of claim 5 , wherein the cold side of the heat deflector lip of the heat shield at least partially defines the channel.

7. The combustor assembly of claim 5 , wherein the channel defines a U-shape.

8. The combustor assembly of claim 5 , wherein the combustor dome comprises a forward wall, wherein the forward wall of the combustor dome defines a direction, wherein the channel defined by the heat deflector lip and the flange defines a height in a direction perpendicular to the direction of the forward wall of the combustor dome, and wherein the height of the channel is at least about 0.025 inches.

9. The combustor assembly of claim 1 , wherein the second side of the combustor dome is a hot side, and wherein the heat deflector lip of the heat shield at least partially covers the outlet of the cooling hole in the combustor dome such that the outer tip of the heat deflector lip is located outward of the outlet of the cooling hole relative to the centerline of the fuel-air injector hardware assembly.

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

11. A combustor assembly for a gas turbine engine, the combustor assembly defining a centerline comprising:
a combustor dome defining an opening and a cooling hole, and at least in part defining a combustion chamber, the combustor dome comprising a first side and a second side, the cooling hole extending from the first side to the second side; and
a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield, the heat shield defining a circumferential channel, the cooling hole in the combustor dome oriented to direct a cooling airflow into the circumferential channel;
wherein the heat shield comprises a heat deflector lip and a flange, wherein a surface of the flange and the heat deflector lip of the heat shield define the channel therebetween configured to receive the cooling airflow from the cooling hole, wherein the cooling hole is oriented to direct the cooling airflow into the channel,
wherein the cooling hole includes an inlet at the first side of the combustor dome and an outlet at the second side of the combustor dome, wherein the heat deflector lip defines an outer tip, and wherein the inlet is positioned a first distance from the centerline and the outer tip of the heat deflector lip is positioned a second distance from the centerline of the combustor assembly, wherein the first distance is greater than the second distance; and
wherein the surface of the flange is flush with the second side of the combustor dome.

12. The combustor assembly of claim 11 , wherein the cooling hole slants towards the opening in the combustor dome from the first side of the combustor dome to the second side of the combustor dome.

13. The combustor assembly of claim 11 , wherein the heat deflector lip includes a hot side and a cold side, and wherein the cold side of the heat deflector lip at least partially defines the circumferential channel.

14. The combustor assembly of claim 11 , wherein the second side of the combustor dome is a hot side, and wherein the heat deflector lip of the heat shield at least partially covers the outlet of the cooling hole in the combustor dome such that the outer tip of the heat deflector lip is located outward of the outlet of the cooling hole relative to the centerline of the combustor assembly.

15. The combustor assembly of claim 11 , wherein the circumferential channel redirects the cooling airflow from the cooling hole along the second side of the combustor dome.

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 1 , wherein the flange is positioned adjacent to the second side of the combustor dome.

18. The combustor assembly of claim 1 , wherein the first side of the combustor dome is a cold side, wherein the second side of the combustor dome is a hot side, and wherein the outlet of the cooling hole is positioned at least partially inward of the outer tip of the heat deflector lip of the heat shield along a direction of the combustor dome.

19. The combustor assembly of claim 1 , wherein the combustor dome further comprises an inner transition portion and an outer transition portion, and wherein a forward wall extends between the inner transition portion and the outer transition portion.

Assignees

• Gen Electric

Inventors

• Hannwacker David Andrew
• Howell Stephen John

Classifications

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R3/283 Primary

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

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/02

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · CPC title