WALL ELEMENT FOR USE IN COMBUSTION APPARATUS

• US 20090100838A1
• Filed: 10/01/2008
• Published: 04/23/2009
• 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: Garry, Ian Murray, Carlisle, Michael Lawrence
• Granted Patent: US 8,113,004 B2
• Time in Patent Office: Days
• 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 for use as part of an inner wall of a gas turbine engine combustor wall structure that has inner and outer walls defining a space therebetween, the wall element comprising deformable cooling pedestals extending into the space and which on contact with the outer wall deform against the outer wall of the wall structure.

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

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

to the inner wall.

4. A wall element according to claim 1, wherein the wall element further comprises a body portion for providing the inner wall of the combustor wall structure and elongate edge portions projecting from the body portion towards the outer wall of the combustor wall structure in use and wherein the pedestal means are provided on the body portion which project in the same direction as and extend beyond the edge portions.

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

6. 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.

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

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

9. A wall element according to any of claims 1, the wall element being for use in a back plate region of a combustor.

10. A wall element according to claim 9, the wall element being generally sector shaped, including spaced radial edges and spaced circumferential edges.

11. A wall structure for a gas turbine engine combustor, the wall structure including inner and outer walls defining a space therebetween, wherein the inner wall includes at least one wall element according to claim 1.

12. A wall structure according to claim 1, wherein the wall structure includes a plurality of wall elements, and edges of the wall elements at least partially overlap.

13. A gas turbine engine combustion chamber comprising a wall element for use as part of an inner wall of a gas turbine engine combustor wall structure that has inner and outer walls defining a space therebetween, the wall element being provided with deformable cooling pedestals extending into the space and which on contact with the outer wall deform against the outer wall of the wall structure.