Liner for a combustor of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017138596-A1
Application number	US-201615221373-A
Country	US
Kind code	A1
Filing date	Jul 27, 2016
Priority date	Jul 28, 2015
Publication date	May 18, 2017
Grant date	—

Abstract

A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a plurality of protrusions and a plurality of recesses. The support member is coupled to the intermediate member at a tangent of each protrusion. Additionally, the liner member is comprised of a ceramic matrix composite material. The liner member is coupled to the intermediate member at a tangent of each recess.

First claim

What is claimed is:

1 . A liner assembly for a combustor, comprising:
a support member; an intermediate member having a plurality of protrusions and a plurality of recesses, the intermediate member being coupled to the support member at a tangent of each protrusion; and a liner member comprised of a ceramic matrix composite material, the liner member being coupled to the intermediate member at a tangent of each recess and defining a combustion chamber of the combustor, wherein the intermediate member is positioned intermediate the support member and the liner member.

2 . The liner assembly of claim 1 , wherein the intermediate member comprises a corrugated metal and the protrusions are defined by a plurality of corrugations of the metal which protrude radially and distally from a centerline of the combustor.

3 . The liner assembly of claim 1 , wherein the support member defines a first passage for a first cooling gas flow and the intermediate member defines a second passage for a second cooling gas flow.

4 . The liner assembly of claim 3 , wherein the support member includes a plurality of apertures defining the first passage for the first cooling gas flow and the intermediate member includes a plurality of apertures defining the second passage for the second cooling gas flow.

5 . The liner assembly of claim 4 , wherein the plurality of apertures of the intermediate member control gas flow through the liner assembly.

6 . The liner assembly of claim 4 , wherein a portion of the intermediate member which includes the plurality of apertures is spaced apart from the liner member and the support member.

7 . The liner assembly of claim 1 , wherein the intermediate member is configured to expand between the support member and the liner member during combustion within the combustor.

8 . The liner assembly of claim 1 , wherein the intermediate member and the support member are comprised of a metallic material.

9 . A liner assembly for a combustor, comprising:
a support member; an intermediate member having a first surface facing the support member and a second surface opposite the first surface; a liner member comprised of a ceramic matrix composite material, wherein the intermediate member is positioned intermediate the support member and the liner member; a first gas passage positioned along the first surface of the intermediate member; and a second gas passage positioned along the second surface of the intermediate member.

10 . The liner assembly of claim 9 , wherein the first gas passage is parallel to the second gas passage.

11 . The liner assembly of claim 9 , wherein at least a portion of gas from the first gas passage flows into the second gas passage.

12 . The liner assembly of claim 9 , wherein the second gas passage controls gas flow through the liner assembly.

13 . The liner assembly of claim 9 , wherein the support member includes a plurality of apertures for receiving gas into the first gas passage and the intermediate member includes a plurality of apertures for receiving gas into the second gas passage.

14 . The liner assembly of claim 9 , wherein the intermediate member is coupled to the support member and to the liner member.

15 . A liner assembly for a combustor, comprising:
a support member including a first plurality of apertures; an intermediate member including a second plurality of apertures; and a liner member comprised of a ceramic matrix composite material, wherein the intermediate member is positioned intermediate the support member and the liner member.

16 . The liner assembly of claim 15 , wherein each of the first plurality of apertures has a diameter greater than a diameter of each of the second plurality of apertures.

17 . The liner assembly of claim 16 , wherein the diameter of each of the first plurality of apertures is between about 0.050-0.300 inches and the diameter of each of the second plurality of apertures is between about 0.020-0.050 inches.

18 . The liner assembly of claim 15 , wherein cooling gas is received through the first plurality of apertures and flows through the second plurality of apertures.

19 . The liner assembly of claim 15 , wherein the second plurality of apertures is longitudinally offset from the first plurality of apertures.

20 . The liner assembly of claim 15 , wherein the intermediate member is coupled to the support member at a position inward of the first plurality of apertures and the intermediate member is coupled to the liner member at a position inward of the second plurality of apertures.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Freeman Ted Joseph
• Varney Bruce E
• Chamberlain Adam L

Classifications

• F05D2250/611

  undulated · CPC title

• F05D2250/61

  corrugated · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/002 Primary

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

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title