MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE

Abstract: a gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. the combustor includes a combustion chamber. the plurality of fuel injects fuel into the combustion chamber of the combustor. the gas turbine engine may include a first fuel circuit and a second fuel circuit. the first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. the second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. the second temperature is less than the first temperature.

Inventor(s): Hejie Li, Shai Birmaher, Michael A. Benjamin

CPC Classification: F02C7/224 (Heating fuel before feeding to the burner)

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