Combustor dome heat shield

Patent metadata

Field	Value
Publication number	US-9746184-B2
Application number	US-201514684891-A
Country	US
Kind code	B2
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

A combustor heat shield comprises a heat shield body adapted to be mounted to a combustor wall with a back side of the heat shield body in spaced-apart facing relationship with the combustor wall to define an air gap between the heat shield body and the combustor wall. At least one nozzle opening is defined in the heat shield bod. The opening is bordered by a nozzle opening boss. The boss extends from the back side of the heat shield body across the air gap for sealing engagement with an adjacent part of the combustor. An annular array of effusion holes is provided adjacent the nozzle opening boss. The effusion holes extend through the heat shield body for passing cooling air from the back side to a front side of the heat shield body. Fins are interspersed between the effusion holes on the back side of the heat shield.

First claim

What is claim is:

1. A heat shield for a combustor of a gas turbine engine, comprising a heat shield body adapted to be mounted to a combustor shell with a back face of the heat shield body in spaced-apart facing relationship with the combustor shell to define an air gap between the heat shield body and the combustor shell, at least one nozzle opening defined in the heat shield body, a nozzle opening boss bordering the at least one fuel nozzle opening and configured for extending from the back face of the heat shield body across the air gap for sealing engagement with an adjacent combustor part, an annular array of effusion holes adjacent the nozzle opening boss, the effusion holes extending through the heat shield body and configured to pass cooling air from the back face to a front face of the heat shield body, and fins interspersed between the effusion holes on the back side of the heat shield, wherein said effusion holes and said fins are located in a non-impingement cooled region of the heat shield, wherein the annular array of effusion holes comprises an inner and an outer annular row of effusion holes, and wherein the fins comprise an inner and outer annular row of fins, the fins of the inner annular row of fins extending in between pairs of adjacent effusion holes of the inner annular row of effusion holes, the fins of the outer annular row of fins extending in between pairs adjacent effusion holes of the outer annular row of effusion holes.

2. The heat shield defined in claim 1 , wherein the effusion holes are aligned tangentially to the at least one fuel nozzle opening.

3. The heat shield defined in claim 1 , wherein an axis of each effusion hole extends at a shallow angle of between 15° and 45° to the plane of the heat shield body.

4. The heat shield defined in claim 2 , wherein each fin is generally aligned tangentially to the fuel nozzle opening and generally parallel to an axis of the adjacent effusion holes.

5. The heat shield defined in claim 1 , wherein the fins are aligned parallel to the adjacent effusion holes.

6. The heat shield defined in claim 1 , wherein the fins have a height which is less than that of the nozzle opening boss.

7. The heat shield defined in claim 1 , wherein the fins of the inner annular row have an inner end which extends from the nozzle opening boss.

8. The heat shield defined in claim 1 , wherein said non-impingement cooled region is surrounded by an impingement cooled region, and wherein said impingement cooled region is in fluid flow communication with said non-impingement cooled region, and wherein heat transfer augmentation features are provided in the impingement cooled region.

9. A combustor for a gas turbine engine, comprising: a combustor shell defining a combustion chamber, a heat shield mounted to the combustor shell with a back face of the heat shield in spaced-apart facing relationship with the combustor shell to define an air gap between the heat shield and the combustor shell, at least one nozzle opening defined in the heat shield; a nozzle opening boss bordering the at least one fuel nozzle opening and extending from the back face of the heat shield across the air gap into sealing engagement with an adjacent combustor part, an annular array of effusion holes around the nozzle opening boss, the effusion holes extending through the heat shield and configured to pass cooling air from the back face to a front face of the heat shield, and fins interspersed between the effusion holes on the back face of the heat shield wherein said effusion holes and said fins are located in a non-impingement cooled region of the heat shield, wherein the annular array of effusion holes comprises an inner and an outer annular row of effusion holes, and wherein the fins comprise an inner and outer annular row of fins, the fins of the inner annular row of fins extending in between pairs of adjacent effusion holes of the inner annular row of effusion holes, the fins of the outer annular row of fins extending in between pairs adjacent effusion holes of the outer annular row of effusion holes.

10. The combustor defined in claim 9 , wherein the adjacent combustor part has a peripheral portion which extends over the non-impingement cooled region of the heat shield around the nozzle opening boss, said peripheral portion blocking impingement jet access to said non-impingement cooled region of the heat shield.

11. The combustor defined in claim 10 , wherein said adjacent part of the combustor is a swirler.

12. The combustor defined in claim 9 , wherein impingement holes are defined in the combustor shell to direct impingement jets over a second region of the back side of the heat shield, said second region surrounding said non-impingement cooled region and being in fluid flow communication therewith.

13. The combustor defined in claim 9 , wherein the effusion holes each has an axis aligned tangentially to the at least one fuel nozzle opening.

14. The combustor defined in claim 9 , wherein the axis of each effusion hole extends at a shallow angle of between 15° and 45° to the plane of the heat shield.

15. The combustor defined in claim 9 , wherein each fin is generally aligned tangentially to the fuel nozzle opening and generally parallel to an axis of the adjacent effusion holes.

16. The combustor defined in claim 9 , wherein the fins are aligned parallel to the adjacent effusion holes.

17. The combustor defined in claim 9 , wherein the fins have a height which is less than that of the nozzle opening boss.

18. The combustor defined in claim 9 , wherein the fins of the inner annular row have an inner end which extends from the nozzle opening boss.

19. A method of cooling a combustor heat shield mounted in a combustor of a gas turbine engine, the method comprising: recuperating impingent air directed over an impingement cooled region of the heat shield and causing it to flow over a non-impingement cooled region surrounded by the impingement cooled region, increasing heat transfer in the non-impingement cooled region by causing the air to flow over fins disposed in the non-impingement cooled region, and effusion cooling the non-impingement cooled region of the heat shield by passing the air through effusion holes defined in the non-impingement cooled region, wherein the annular array of effusion holes comprises an inner and an outer annular row of effusion holes, and wherein the fins comprise an inner and outer annular row of fins, the fins of the inner annular row of fins extending in between pairs of adjacent effusion holes of the inner annular row of effusion holes, the fins of the outer annular row of fins extending in between pairs adjacent effusion holes of the outer annular row of effusion holes.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael
• Sze Robert

Classifications

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/10 Primary

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/26

  Controlling the air flow · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title