Combustor assembly

Patent metadata

Field	Value
Publication number	US-10281153-B2
Application number	US-201615053460-A
Country	US
Kind code	B2
Filing date	Feb 25, 2016
Priority date	Feb 25, 2016
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A combustor assembly includes a first combustion chamber member and a second combustion chamber member. The first and second combustion chamber members are each formed of a CMC material and include adjacently positioned coupling flanges. A mounting assembly includes a pair of mounting flanges positioned on opposite sides of the coupling flanges of first and second combustion chamber members. An attachment member of the mounting assembly clamps the pair of mounting flanges together to mount the first and second combustion chamber members.

First claim

What is claimed is:

1. A combustor assembly for a gas turbine engine defining an axial direction and a circumferential direction, the combustor assembly comprising:
a first combustion chamber member and a second combustion chamber member, the first and second combustion chamber members each formed of a ceramic matrix composite material and together defining at least in part a combustion chamber, the first combustion chamber member comprising a first coupling flange and the second combustion chamber member comprising a second coupling flange, the first and second coupling flanges positioned adjacent to one another and extending outward from the combustion chamber; and
a mounting assembly comprising a first mounting flange and a second mounting flange, the first mounting flange positioned adjacent to the first coupling flange and the second mounting flange positioned adjacent to the second coupling flange, the mounting assembly further comprising an attachment member attaching the first and second combustion chamber members and clamping the first mounting flange and the second mounting flange together to attach the first combustion chamber member and the second combustion chamber member;
wherein the mounting assembly supports the combustor assembly within the gas turbine engine;
wherein the first combustion chamber member is a combustor dome and wherein the second combustion chamber member is a combustion chamber liner;
wherein the first and second mounting flanges of the mounting assembly extend substantially continuously in the circumferential direction;
wherein the attachment member comprises a nut and a bolt, the attachment member extending through the first and second mounting flanges and the first and second coupling flanges.

2. The combustor assembly of claim 1 , wherein the combustion chamber liner is a combustion chamber inner liner.

3. The combustor assembly of claim 1 , wherein the attachment member presses the first mounting flange towards the second mounting flange.

4. The combustor assembly of claim 3 , wherein the mounting assembly further comprises a bushing extending around the bolt within the first and second coupling flanges.

5. The combustor assembly of claim 4 , wherein the bushing defines a length, wherein the first and second coupling flanges define a combined width, and wherein the length of the bushing is less than the combined width of the first and second coupling flanges.

6. The combustor assembly of claim 1 , wherein the first and second coupling flanges extend substantially continuously in the circumferential direction, and wherein the first and second coupling flanges further extend outward from the combustion chamber substantially along a radial direction of the gas turbine engine.

7. The combustor assembly of claim 1 , wherein the second mounting flange further extends outward from the combustion chamber substantially along a radial direction of the gas turbine engine.

8. The combustor assembly of claim 1 , wherein the first and second mounting flanges of the mounting assembly are comprised of a metal material.

9. The combustor assembly of claim 1 , wherein the mounting assembly further comprises an annular support member extending from a forward end to an aft end, wherein the second mounting flange extends from the forward end of the annular support member, and wherein the annular support member includes a coupling at the aft end for mounting the support member within the gas turbine engine.

10. The combustor assembly of claim 9 , wherein the annular support member includes a plurality of gaps extending generally along the axial direction to allow for expansion of the first and second combustion chamber members relative to the annular support member of the mounting assembly.

11. A combustor assembly for a gas turbine engine defining an axial direction and a circumferential direction, the combustor assembly comprising:
a combustor dome formed of a ceramic matrix composite material and comprising a first coupling flange;
a liner formed of a ceramic matrix composite material and comprising a second coupling flange, the liner and the combustor dome together defining at least in part a combustion chamber; and
a mounting assembly comprising a first mounting flange and a second mounting flange, the first mounting flange positioned adjacent to the first coupling flange and the second mounting flange positioned adjacent to the second coupling flange, the mounting assembly further comprising an attachment member clamping the first mounting flange and the second mounting flange together to attach the liner and combustor dome;
wherein the attachment member comprises a nut and a bolt, the attachment member extending through the first and second mounting flanges and the first and second coupling flanges;
wherein the first and second mounting flanges of the mounting assembly extend substantially continuously in the circumferential direction.

12. The combustor assembly of claim 11 , wherein the mounting assembly supports the combustor assembly within the gas turbine engine.

13. The combustor assembly of claim 11 , wherein the first and second coupling flanges extend substantially continuously in the circumferential direction.

14. The combustor assembly of claim 11 , wherein the mounting assembly further comprises an annular support member extending from a forward end to an aft end, wherein the second mounting flange extends from the forward end of the annular support member, and wherein the annular support member includes a coupling at the aft end for mounting the support member within the gas turbine engine.

15. A gas turbine engine defining an axial direction and a circumferential direction, the gas turbine engine comprising:
a compressor section;
a turbine section;
a combustion section disposed between the compressor section and the turbine section, the combustion section comprising a combustor assembly, the combustor assembly comprising a first combustion chamber member and a second combustion chamber member, the first and second combustion chamber members each formed of a ceramic matrix composite material and together defining at least in part a combustion chamber, the first combustion chamber member comprising a first coupling flange and the second combustion chamber member comprising a second coupling flange, the first and second coupling flanges positioned adjacent to one another and extending outward from the combustion chamber; and
a mounting assembly comprising a first mounting flange and a support member including a second mounting flange, the first and second mounting flanges disposed on opposite sides of the first and second coupling flanges to attach the first and second combustion chamber members, the support member attached to a structural component of the gas turbine engine to support the combustor assembly,
wherein the mounting assembly further comprises an attachment member pressing the first mounting flange towards the second mounting flange;
wherein the first combustion chamber member is a combustor dome and wherein the second combustion chamber member is a combustion chamber liner;
wherein the first and second mounting flanges of the mounting assembly extend substantially continuously in the circumferential direction;
wherein the attachment member comprises a nut and a bolt, the attachment member extending through the first and second mounting flanges and the first and second coupling flanges.

16. The combustor assembly of claim 1 , wherein the mounting assembly further comprises a support member including the second mounting flange, the support mem

Assignees

• Gen Electric

Inventors

• Hannwacker David Andrew
• Howell Stephen John

Classifications

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/52

  Toroidal combustion chambers · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title