FIELD: machine building.
SUBSTANCE: described is fuel nozzle (310) for combustion chamber of gas turbine unit. Fuel injector (310) comprises flange (312), nozzle ledge (315), hollow body (320), gas fuel channel (322), gas fuel union (317) and gas fuel heat shield (380). Protrusion (315) for nozzles is released from flange (312). Hollow body (320) extends from flange (312). Gas fuel channel (322) extends through hollow body (320). Gas fuel connection (317) is connected to nozzle ledge (315). Heat shield of gas fuel (380) extends from nozzle (317) of gas fuel at least partially through channel (322) of gas fuel. Size-selected heat shield (380) of the gas fuel forms gap (389) between the heat shield of gas fuel (380) and hollow body (320) along the gas fuel channel (322).
EFFECT: disclosed is a heat-insulated fuel nozzle for a gas turbine engine.
8 cl, 4 dwg
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