Wall element for use in combustion apparatus

• US 8,113,004 B2
• Filed: 10/01/2008
• Issued: 02/14/2012
• Est. Priority Date: 10/23/2007
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Carlisle, Michael Lawrence, Garry, Ian Murray
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Meade, Lorne
• Application Number:
  US12/243,002
• Publication Number:
  US 20090100838A1
• Time in Patent Office: 1,231 Days
• Field of Search: 60752-760, 608/00, 110336-340, 431/350, 431/351, 431/353, 165/81, 165/154
• US Class Current: 60/752
• CPC Class Codes: F23R 2900/00005 Preventing fatigue failures or reducing mechanical stress in gas turbine components
• CPC Class Codes: F23R 3/00 Continuous combustion chambers using liquid or gaseous fuel
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence

Abstract

A tile for use as part of an inner wall of a gas turbine engine combustor, the tile being provided with deformable cooling pedestals extending into a space between the tile and the outer wall. The pedestals are deformed in contact with the outer wall of the combustor.

Claims

1. A wall element connected with a gas turbine engine combustor wall that has an inner surface and an outer surface, the wall element and the inner surface defining a space therebetween, the wall element comprising deformable cooling pedestals extending into the space and which on contact with the inner surface deform against the inner surface of the combustor wall, wherein the wall element further comprises a body portion and elongate edge portions projecting from the body portion towards the inner surface of the combustor wall and wherein the deformable cooling pedestals are provided on the body portion which project in the same direction as and extend beyond the edge portions into the space.

2. A wall element according to claim 1, further comprising fastening elements for securing the wall element to the combustor wall.

3. A wall element according to claim 1, wherein the pedestals are at an angle other than 90°

to the inner surface.

4. A wall element according to claim 1, wherein the pedestals have the form of a helical or omega spring.

5. A wall element according to claim 1, wherein the wall element is generally rectangular and further comprises axial and circumferential edges, the axial edges being generally oriented in an axial direction of the gas turbine engine combustor in use and the circumferential edges being generally oriented in a circumferential direction of the gas turbine engine combustor in use.

6. A wall element according to claim 5, wherein seal means are provided on or near the axial edges of the wall element.

7. A wall element according to claim 5, wherein seal means are provided on or near the circumferential edges of the wall element.

8. A wall element according to claim 1, the wall element being for use in a back plate region of a combustor, the wall element being generally sector shaped, including spaced radial edges and spaced circumferential edges.

9. A gas turbine combustor wall structure comprising:

a combustor wall; and

a plurality of discrete tiles attached to the combustor wall on the combustion side, there being a space formed between each discrete tile and the combustor wall;

each of the discrete tiles provided with deformable cooling pedestals extending into the space;

the cooling pedestals deforming laterally when contacting the combustor wall, wherein discrete tile edges overlap.

10. A gas turbine engine combustion chamber comprising:

a combustor wall with discrete tiles attached to an inner surface of the combustor wall, the discrete tiles and the inner surface defining a space therebetween, the discrete tiles provided with deformable cooling pedestals extending into the space and which on contact with the inner surface of the combustor wall deform against the inner surface.