Abstract: A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut. A gas turbine engine is provided that includes a multiple of fuel injectors in communication with a combustor and a cooling system in communication with each of the multiple of fuel injectors.

Abstract: A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced.

Abstract: An assembly is provided for a turbine engine. The assembly includes a cooling tube through which a flow path extends. The assembly also includes a fuel injector, which includes a stem connected to a tip. The stem is arranged within the cooling tube. The tip extends from the cooling tube to a nozzle. The cooling tube is adapted to direct cooling air through the flow path.

Abstract: A de-oiler balance weight for a rotor disk stack susceptible to collecting oil is provided. The rotor disk stack is configured for use in a gas turbine engine. The de-oiler balance weight comprises a front wall having a first mounting aperture and a first outboard end. An aft wall has a second mounting aperture and a second outboard end. An inboard wall connects the front wall and the aft wall and defines a recess therebetween that is configured to receive a flange portion of a rotor disk in the rotor disk stack. A channel extends at least partially through the de-oiler balance weight for directing the oil away from the rotor disk stack.

Abstract: A de-oiler balance weight for a rotor disk stack susceptible to collecting oil is provided. The rotor disk stack is configured for use in a gas turbine engine. The de-oiler balance weight comprises a front wall having a first mounting aperture and a first outboard end. An aft wall has a second mounting aperture and a second outboard end. An inboard wall connects the front wall and the aft wall and defines a recess therebetween that is configured to receive a flange portion of a rotor disk in the rotor disk stack. A channel extends at least partially through the de-oiler balance weight for directing the oil away from the rotor disk stack.

Abstract: A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced.

Abstract: An assembly is provided for a turbine engine. The assembly includes a cooling tube through which a flow path extends. The assembly also includes a fuel injector, which includes a stem connected to a tip. The stem is arranged within the cooling tube. The tip extends from the cooling tube to a nozzle. The cooling tube is adapted to direct cooling air through the flow path.

Abstract: A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut. A gas turbine engine is provided that includes a multiple of fuel injectors in communication with a combustor and a cooling system in communication with each of the multiple of fuel injectors.