Combustor heat shield

Patent metadata

Field	Value
Publication number	US-9557060-B2
Application number	US-201414305404-A
Country	US
Kind code	B2
Filing date	Jun 16, 2014
Priority date	Jun 16, 2014
Publication date	Jan 31, 2017
Grant date	Jan 31, 2017

Abstract

A heat shield for a combustor of a gas turbine engine has a heat shield adapted to be mounted to a combustor wall with a back face of the heat shield in spaced-apart facing relationship with an inner surface of the combustor wall to define an air space. Concentric rails extend from the back face of the heat shield across the air space surrounding a nozzle opening in the heat shield. Effusion holes are provided between the concentric rails and extend between the back and front faces. Fins may be placed between the effusion holes.

First claim

What is claimed 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 wall with a back side of the heat shield body in spaced-apart facing relationship with an inner surface of the combustor wall to define an air space between the heat shield body and the combustor wall, at least one nozzle opening defined in the heat shield body; rails extending from the back side of the heat shield body across the air space, the rails including a pair of concentric, spaced apart rings defining a toroidal region, effusion holes located in the toroidal region and through the heat shield body and configured to pass cooling air from the back side to a front side of the heat shield, and elongated fins interspersed between the effusion holes in the toroidal region, wherein each fin of the elongated fins are extending from one ring of the spaced apart rings, and wherein each fin are arranged in the toroidal region extending with a tangential component relative to the nozzle opening.

2. The heat shield defined in claim 1 , wherein the effusion holes each has an axis aligned tangentially to the nozzle opening.

3. The heat shield defined in claim 2 , wherein the axis of each effusion hole extends at a shallow angle of between 20° and 35° to the plane of the heat shield.

4. The heat shield defined in claim 1 , wherein each elongated fin is disposed between adjacent effusion holes.

5. The heat shield defined in claim 1 , wherein the pair of concentric rings includes an inner ring located at the periphery of the nozzle opening and an outer ring.

6. The heat shield defined in claim 5 , wherein the inner ring and the elongated fins are at a height wherein the inner rail and fins come into contact with selected components of the dome.

7. The heat shield defined in claim 6 , wherein the selected components includes a floating collar surrounding the nozzle.

8. The heat shield defined in claim 6 , wherein the outer ring has a height greater than the inner ring and is adapted to contact the dome so as to form an annular cooling air gap with the inner ring and the dome for the purpose of receiving cooling air from beyond the dome and passing through openings in the dome.

9. The heat shield defined in claim 4 wherein the elongated fins comprises an outer row of fins for promoting air turbulence within the toroidal region.

10. A heat shield for a combustor of a gas turbine engine, comprising a heat shield body adapted to be mounted to a combustor wall with a back face of the heat shield body in spaced-apart facing relationship with an inner surface of the combustor wall to define an air space between the heat shield body and the combustor wall, at least one fuel nozzle opening defined in the heat shield body, inner and outer concentric rails extending from the back face of the heat shield body across the air space surrounding each fuel nozzle opening, a plurality of effusion holes formed between the inner and outer rails and directed tangentially to the respective fuel nozzle opening, and elongated fins extending between adjacent effusion openings, each fin of the elongated fins are extending from at least one of the inner and outer rails towards an opposite one of the inner and outer rails and wherein each fin are arranged in the toroidal region extending with a tangential component relative to the nozzle opening.

11. The heat shield defined in claim 10 , wherein the axis of each effusion hole is in the range of 20° and 35° to the plane of the heat shield.

12. The heat shield defined in claim 10 , wherein the fins include first and second rows of circumferentially spaced-apart fins, the fins of the second row being circumferentially staggered relative to the fins of the first row.

13. The heat shield defined in claim 12 , wherein the second row surrounds the first row, and wherein the fins of the second row are shorter than the fins of the first row.

14. The heat shield defined in claim 13 , wherein the fins of the second row project inwardly from the outer rail, and wherein the fins of the first row project outwardly from the inner ring.

15. A heat shield for a combustor of a gas turbine engine, comprising: a heat shield body adapted to be mounted to a combustor wall with a back face of the heat shield body in spaced-apart facing relationship with an inner surface of the combustor wall to define an air space between the heat shield body and the combustor wall, at least one fuel nozzle opening defined in the heat shield body, inner and outer concentric rails extending from the back face of the heat shield body and surrounding the at least one fuel nozzle opening, a plurality of effusion holes extending through the heat shield body between the inner and outer rails, and elongated fins extending from the back face of the heat shield body between the inner and outer rails, the elongated fins including first and second rows of circumferentially spaced-apart fins, the fins of the second row being circumferentially staggered relative to the fins of the first row, wherein the second row surrounds the first row, and wherein the fins of the second row are shorter than the fins of the first row.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael
• Sze Robert

Classifications

• F23R3/002

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

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/04 Primary

  Air inlet arrangements · CPC title

• Y02T50/60

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