Gas turbine engine combustor assembly having integrated control valves
AssigneeGeneral Electric Company
InventorsGeoffrey David Myers, Lewis Berkley Davis, Jr., Joseph Citeno
Life of this patent
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Abstract
A combustor assembly for a gas turbine engine includes a combustor endcover having at least one fuel circuit and mounted thereto a plurality of pre-mixers and at least one control valve. The at least one control valve is fluidly connected to the at least one fuel circuit and operatively connected to a controller. The controller selectively operates the at least one control valve to deliver fuel through the at least one fuel circuit to the plurality of pre-mixers in order to achieve an enhanced level of operational flexibility by providing individual combustion chamber control.
Claims11
A combustor assembly for a gas turbine engine comprising:
- a combustor endcover;
- at least one fuel circuit arranged within the combustion endcover;
- a plurality of pre-mixers mounted to the combustor endcover;
- at least one control valve arranged within the combustor endcover, said at least one control valve being operatively associated with the at least one fuel circuit;
- and
- a controller selectively operating the at least one control valve to pass fuel to the at least one fuel circuit to deliver the fuel to the plurality of pre-mixers, wherein the controller selectively operates the at least one control valve based upon an operating parameter of the gas turbine engine.
Dependencies are inferred from the claim text.