Combustor assembly
AssigneeGeneral Electric Company
InventorsDavid Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
Life of this patent
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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.
Claims17
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.
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.
Dependencies are inferred from the claim text.