Combustor Assembly
AssigneeGeneral Electric Company
InventorsDavid Andrew Hannwacker, Stephen John Howell
Life of this patent
Estimating the term…
Abstract
A combustor assembly for a gas turbine engine includes a combustor dome defining an opening, a cooling hole, and at least in part defining a combustion chamber. The combustor dome includes a first side and a second side, the cooling hole extending from the first side to the second side. The combustor assembly additionally includes a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and including a heat shield. The heat shield includes a heat deflector lip. The cooling hole in the combustor dome is oriented to direct a cooling airflow onto the heat deflector lip to maintain at least a portion of the heat shield within a desired operating temperature range.
Claims20
A combustor assembly for a gas turbine engine, the combustor assembly comprising:
- a combustor dome defining an opening and a cooling hole, and at least partially defining a combustion chamber, the combustor dome comprising a first side and a second side, the cooling hole extending from the first side to the second side;
- and
- a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield, the heat shield comprising a heat deflector lip, and the cooling hole in the combustor dome oriented to direct a cooling airflow onto the heat deflector lip.
A combustor assembly for a gas turbine engine, the combustor assembly comprising:
- a combustor dome defining an opening and a cooling hole, and at least in part defining a combustion chamber, the combustor dome comprising a first side and a second side, the cooling hole extending from the first side to the second side;
- and
- a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield, the heat shield defining a circumferential channel, the cooling hole in the combustor dome oriented to direct a cooling airflow into the circumferential channel.
A method for cooling a combustor of a gas turbine engine, the combustor including a combustor dome, the method comprising:
- providing a cooling airflow to a cooling hole extending from a cold side of the combustor dome to a hot side of the combustor dome, the combustor dome defining an opening and the combustor comprising a fuel-air injector hardware assembly extending at least partially through the opening;
- and
- directing the cooling airflow from the cooling hole to a cold side of a heat deflector lip of a heat shield of the fuel-air injector hardware assembly, the heat deflector lip located within a combustion chamber of the combustor.
Dependencies are inferred from the claim text.