Combustor Assembly
AssigneeGeneral Electric Company
InventorsDavid Andrew Hannwacker, Stephen John Howell
Life of this patent
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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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.