Liner for a combustor of a gas turbine engine with metallic corrugated member

Patent metadata

Field	Value
Publication number	US-11619387-B2
Application number	US-201615221373-A
Country	US
Kind code	B2
Filing date	Jul 27, 2016
Priority date	Jul 28, 2015
Publication date	Apr 4, 2023
Grant date	Apr 4, 2023

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, each of the plurality of protrusions circumferentially alternating with each of the plurality of recesses, the intermediate member being coupled to the support member at a tangent of each of the plurality of protrusions, wherein the tangent is located at the most radially distal point, from a centerline of the liner assembly, of each of the plurality of protrusions; and
a liner member comprised of a plurality of tiles spaced apart by open passages and supported by the intermediate member, each of the plurality of tiles comprised of a ceramic matrix composite material, the liner member being coupled to the intermediate member at a tangent of each of the plurality of recesses and defining a combustion chamber of the combustor, wherein the tangent is located at the most radially proximal point, from the centerline, of each of the plurality of recesses,
wherein the intermediate member is positioned intermediate the support member and the liner member and includes a plurality of apertures,
wherein the plurality of apertures are spaced apart from the support member, and
wherein each of the plurality of apertures is radially between the plurality of protrusions and the plurality of recesses.

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

3. The liner assembly of claim 1 , wherein the support member with the intermediate member define a first passage and the intermediate member with the liner member define a second passage.

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

5. The liner assembly of claim 4 , wherein the plurality of apertures of the intermediate member have smaller flow areas than that of the plurality of apertures of the support member and thus control flow of the gas from the second passage towards the liner member.

6. The liner assembly of claim 1 , 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. The liner assembly of claim 1 , wherein the intermediate member comprises an extension between each of the plurality of protrusions and each adjacent one of the plurality of recesses, and wherein each of the plurality of apertures is disposed in one of the extensions and does not abut the liner member nor the support member.

10. 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, wherein the intermediate member comprises a plurality of protrusions and a plurality of recesses, each of the plurality of protrusions circumferentially alternating with each of the plurality of recesses, the intermediate member supported by the support member at the most radially distal point, from a centerline of the liner assembly, of each of the plurality of protrusions;
a liner member comprised of a plurality of tiles spaced apart by open passages and supported by the intermediate member at the most radially proximal point, from the centerline, of each of the plurality of recesses, each of the plurality of tiles comprised of a ceramic matrix composite material, wherein the intermediate member is positioned intermediate the support member and the liner member, wherein the liner member defines a combustion chamber of the combustor;
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,
wherein the intermediate member comprises a plurality of apertures to direct at least a portion of a first cooling gas flowing through the first gas passage into the second gas passage, and the open passages allow the portion of the first cooling gas flowing through the second gas passage to flow into the combustion chamber, wherein the plurality of apertures are spaced apart from the support member, and
wherein each of the plurality of apertures is radially between the plurality of protrusions and the plurality of recesses.

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

12. The liner assembly of claim 10 , wherein the plurality of apertures in the intermediate member control the first cooling gas flow through the liner assembly.

13. The liner assembly of claim 9 , wherein the support member includes a plurality of apertures for receiving the first cooling gas into the first 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. The liner assembly of dam 10 , wherein the intermediate member has a coefficient of thermal expansion 2-4 times greater than the coefficient of thermal expansion of the liner member.

16. 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 spaced apart from the support member, wherein the intermediate member comprises a plurality of protrusions and a plurality of recesses, each of the plurality of protrusions circumferentially alternating with each of the plurality of recesses, the intermediate member supported by the support member at the most radially distal point, from a centerline of the liner assembly, of each of the plurality of protrusions, wherein each of the second plurality of apertures is radially between the plurality of protrusions and the plurality of recesses; and
a liner member comprised of a plurality of tiles spaced apart by open passages and supported by the intermediate member at the most radially proximal point, from the centerline, of each of the plurality of recesses, each of the plurality of tiles comprised of a ceramic matrix composite material, wherein the liner member defines a combustion chamber of the combustor, wherein the intermediate member is positioned intermediate the support member and the liner member.

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

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

19. The liner assembly of claim 16 , wherein cooling gas is received through the first plurality of apertures and flows through the second plurality of apertures, and wherein the open passages allow the cooling gas flowing through the second plurality of apertures to flow into the combustion chamber.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

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

Classifications

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title

• F05D2250/611

  undulated · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F05D2250/61

  corrugated · CPC title