Combustor assembly

Patent metadata

Field	Value
Publication number	US-10378771-B2
Application number	US-201615053484-A
Country	US
Kind code	B2
Filing date	Feb 25, 2016
Priority date	Feb 25, 2016
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.

First claim

What is claimed is:

1. A combustor assembly for a gas turbine engine defining an axial direction and a radial direction and including a structural component, the combustor assembly comprising:
a combustor dome;
a liner attached to or formed integrally with the combustor dome and extending between a forward end and an aft end, the combustor dome and liner together defining at least in part a combustion chamber, the liner defining a coupling flange extending outward from the combustion chamber generally along the radial direction; and
a mounting assembly attached to the coupling flange of the liner proximate the forward end of the liner for supporting the combustor dome and liner within the gas turbine engine relative to the structural component of the gas turbine engine;
wherein the mounting assembly includes a support member extending from a forward end to an aft end, wherein the forward end of the support member is attached to the liner proximate the forward end of the liner, and wherein the aft end of the support member is configured for attachment to the structural component of the gas turbine engine;
wherein the support member is comprised of a metal material, wherein the liner is comprised of a ceramic matrix composite material, and wherein the combustor dome is comprised of a ceramic matrix composite material; and
wherein the mounting assembly includes a fastener extending through the coupling flange of the liner.

2. The combustor assembly of claim 1 , wherein the support member extends substantially continuously along a circumferential direction to define an annular shape.

3. The combustor assembly of claim 2 , wherein the support member includes a plurality of gaps extending generally along the axial direction to allow for thermal expansion of at least one of the liner or the combustor dome relative to the support member of the mounting assembly.

4. The combustor assembly of claim 2 , wherein the support member defines a length along the axial direction, wherein the support member includes a plurality of gaps, and wherein each of the plurality of gaps extend along at least about fifty percent of the length of the support member.

5. The combustor assembly of claim 2 , wherein the support member includes a plurality of gaps to allow for thermal expansion of at least one of the liner or the combustor dome relative to the support member of the mounting assembly, and wherein each of the plurality of gaps define a minimum width of at least about 0.05 inches.

6. The combustor assembly of claim 1 , wherein the coupling flange is positioned at the forward end of the liner, wherein the combustor dome also includes a coupling flange extending outward relative to the combustion chamber generally along the radial direction and positioned adjacent to the coupling flange of the liner, and wherein the mounting assembly attaches the coupling flange of the liner to the coupling flange of the combustor dome.

7. The combustor assembly of claim 6 , wherein the mounting assembly comprises a second mounting flange positioned adjacent to the coupling flange of the liner and a first mounting flange positioned adjacent to the coupling flange of the combustor dome, and wherein the mounting assembly further comprises an attachment member for pressing the first mounting flange towards the second mounting flange to attach the liner to the combustor dome.

8. The combustor assembly of claim 7 , wherein the support member includes the second mounting flange at the forward end of the support member.

9. The combustor assembly of claim 1 , wherein the liner is an inner liner.

10. A gas turbine engine defining an axial direction, a radial 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 combustor dome and a liner extending between a forward end and an aft end, the combustor dome and liner together defining at least in part a combustion chamber, the liner defining a coupling flange extending outward from the combustion chamber generally along the radial direction; and
a mounting assembly including a support member extending between a forward end and an aft end, the forward end of the support member attached to the liner proximate the forward end of the liner and the aft end of the support member attached to a structural component of the gas turbine engine to support the combustor assembly, wherein the mounting assembly includes a fastener extending through the coupling flange of the liner;
wherein the support member is comprised of a metal material, wherein the liner is comprised of a ceramic matrix composite material, and wherein the combustor dome is comprised of a ceramic matrix composite material.

11. The gas turbine engine of claim 10 , wherein the support member extends substantially continuously along the circumferential direction to define an annular shape.

12. The gas turbine engine of claim 10 , wherein the support member includes a plurality of gaps extending generally along the axial direction to allow for expansion of at least one of the liner or the combustor dome relative to the support member of the mounting assembly.

13. The gas turbine engine of claim 10 , wherein the structural component is configured as at least one of an inner combustor casing, an outer combustor casing, a turbine casing, or a turbine frame member.

14. The gas turbine engine of claim 10 , wherein the combustor dome includes a coupling flange extending outward relative to the combustion chamber and positioned adjacent to the coupling flange of the liner, and wherein the mounting assembly attaches the coupling flange of the liner to the coupling flange of the combustor dome.

15. The gas turbine engine of claim 14 , wherein the mounting assembly comprises a second mounting flange positioned adjacent to the coupling flange of the liner, wherein the support member comprises a first mounting flange positioned adjacent to the coupling flange of the combustor dome, and wherein the mounting assembly further comprises an attachment member for pressing the first mounting flange towards the second mounting flange to attach the liner to the combustor dome.

16. The combustor assembly of claim 1 , wherein the combustor assembly defines a length generally along the axial direction, and wherein the mounting assembly is attached to the liner within at least about the forward thirty percent of the combustor assembly length.

17. The gas turbine engine of claim 10 , wherein the forward end of the support member is attached to the coupling flange of the liner proximate the forward end of the liner.

Assignees

• Gen Electric

Inventors

• Hannwacker David Andrew
• Howell Stephen John
• Jacobson John Carl

Classifications

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F02C7/20

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

• F23R3/50 Primary

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title