Shell and tiled liner arrangement for a combustor

Patent metadata

Field	Value
Publication number	US-9651258-B2
Application number	US-201314134840-A
Country	US
Kind code	B2
Filing date	Dec 19, 2013
Priority date	Mar 15, 2013
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles.

First claim

What is claimed is:

1. A combustor for use in a gas turbine engine, the combustor comprising
an annular metallic shell forming an annular cavity, and
an annular liner arranged in the annular cavity of the annular metallic shell and defining an annular combustion chamber, the annular liner including a first ceramic tile coupled to the metallic shell by a first fastener extending through the first ceramic tile and a second ceramic tile coupled to the metallic shell by a second fastener extending through the second ceramic tile,
wherein an overlapped portion of the first ceramic tile is arranged to extend between the second fastener that extends through the second ceramic tile and the annular combustion chamber to shield the second fastener from the annular combustion chamber,
wherein the annular metallic shell is formed to include portions that define dimples, the portions that define the dimples extending outward in a radial direction away from a central axis of the combustor around which the combustion chamber extends.

2. The combustor of claim 1 , further comprising a heat shield arranged to extend between the first fastener that extends through the first ceramic tile and the annular combustion chamber to shield the first fastener from the annular combustion chamber.

3. The combustor of claim 1 , wherein the annular metallic shell is formed to include joggles extending inwardly in a radial direction toward a central axis of the combustor around which the combustion chamber extends.

4. The combustor of claim 1 , wherein the first ceramic tile is formed to include a radially-inwardly opening hollow sized and arranged to receive at least a portion of one of the dimples included in the annular metallic shell.

5. The combustor of claim 4 , wherein the second ceramic tile is formed to include a radially-inwardly opening hollow sized and arranged to receive at least a portion of another one of the dimples included in the annular metallic shell.

6. The combustor of claim 1 , wherein the first fastener and the second fastener are formed to include passages configured to receive active cooling air.

7. The combustor of claim 2 , further comprising at least one fuel nozzle arranged to inject fuel into the annular combustion chamber.

8. The combustor of claim 1 , wherein the second ceramic tile includes a body and at least one tab extending from the body.

9. A combustor for use in a gas turbine engine, the combustor comprising
an annular metallic shell forming an annular cavity, and
an annular ceramic tiled liner arranged in the annular cavity of the annular metallic shell and defining an annular combustion chamber, the annular ceramic tiled liner including a first ceramic tile coupled to the metallic shell by a first fastener extending through the first ceramic tile and a second ceramic tile coupled to the metallic shell by a second fastener extending through the second ceramic tile,
wherein a portion of the first ceramic tile is arranged to overlap the second fastener that extends through the second ceramic tile and a portion of the second ceramic tile arranged around the second fastener to shelter the second fastener and the portion around the second fastener from heat generated in the annular combustion chamber,
wherein the annular ceramic tiled liner includes a last ceramic tile, the annular metallic shell includes a V-shaped notch in which the last ceramic tile is received, and the last ceramic tile includes a curled portion that is received in the V-shaped notch.

10. The combustor of claim 9 , wherein the first and second ceramic tiles include interlocking tabs and the interlocking tabs are positioned between the first or second ceramic tile and the annular metallic shell.

11. The combustor of claim 10 , wherein the interlocking tabs extend circumferentially around the annular combustion chamber.

12. The combustor of claim 10 , wherein the first and second ceramic tiles are formed from a ceramic matrix composite material and the first and second ceramic tiles are formed without cutting or joining fibers of the ceramic matrix composite material such that the first and second ceramic tiles are essentially two-dimensional.

13. The combustor of claim 10 , wherein the interlocking tabs extend longitudinally along the annular combustion chamber.

14. The combustor of claim 9 , wherein each fastener used to secure one of the first and second ceramic tiles is arranged proximate to one end of each of the corresponding first and second ceramic tiles.

15. The combustor of claim 14 , wherein the first and second ceramic tiles include interlocking tabs and the interlocking tabs are positioned between the first or second ceramic tile and the annular metallic shell.

Assignees

• Rolls Royce Corp

Inventors

• Graves Charles B
• Cummings Iii William G
• Bennett Russell N
• Shi Jun

Classifications

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F23R3/002 Primary

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

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title