Abstract: A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

Abstract: A method and apparatus for a crimp pin electrical connector can include a body with a first face and a second face, with openings extending through the body from the first face to the second face. A grommet can connect to the body with grommet holes aligned with the openings. A cap having a set of cap holes can align with the grommet holes. A nut can threadably engage with the body to compress the grommet via the cap to seal wires connected to the body with an interference.

Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.

Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

Abstract: A method and apparatus for a crimp pin electrical connector can include a body with a first face and a second face, with openings extending through the body from the first face to the second face. A grommet can connect to the body with grommet holes aligned with the openings. A cap having a set of cap holes can align with the grommet holes. A nut can threadably engage with the body to compress the grommet via the cap to seal wires connected to the body with an interference.

Abstract: A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

Abstract: An engine includes a combustion section and a fuel delivery system in fluid communication with the combustion section for providing fuel to the combustion section. The fuel delivery system includes a fuel oxygen reduction unit defining a circulation gas flowpath. The fuel oxygen reduction unit includes a gas oxygen reduction unit positioned in the circulation gas flowpath for reducing an oxygen content of a flow of stripping gas through the circulation gas flowpath and a pre-heater positioned in thermal communication with the circulation gas flowpath upstream of the gas oxygen reduction unit.

Abstract: A fuel oxygen conversion unit includes a contactor; a fuel gas separator, the fuel oxygen conversion unit defining a circulation gas flowpath from the fuel gas separator to the contactor; and an isolation valve in airflow communication with the circulation gas flowpath for modulating a gas flow through the circulation gas flowpath to the contactor.

Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

Abstract: A fuel system for an aircraft includes a fuel source and a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path and stripping gas supply path are each in airflow communication with the fuel source.

Abstract: A fuel oxygen conversion unit for a vehicle or an engine of the vehicle includes a contactor; a mechanically-driven, first fuel gas separator defining a liquid fuel outlet and a stripping gas outlet, the fuel oxygen conversion unit defining a liquid fuel outlet path in fluid communication with the liquid fuel outlet of the first fuel gas separator; and a second fuel gas separator positioned in fluid communication with the liquid fuel outlet path at a location downstream of the first fuel gas separator.

Abstract: An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

Abstract: A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet. The fuel oxygen conversion unit also includes a fuel/gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor, an axial direction, and a radial direction. The fuel/gas separator includes a separator assembly including a core including a gas-permeable section extending along the axial direction and defining a maximum diameter, the maximum diameter of the gas-permeable section being substantially constant along the axial direction; and a stationary casing, the fuel/gas separator defining a fuel/gas chamber in fluid communication with the fuel/gas mixture inlet at a location inward of the stationary casing and outward of the gas-permeable section of the separator assembly along the radial direction.

Abstract: A method of operating a fuel oxygen reduction unit for a vehicle or a gas turbine engine of the vehicle is provided. The fuel oxygen reduction unit including a contactor and a fuel gas separator, and further defining a stripping gas flowpath in flow communication with a stripping gas inlet of the contactor and a stripping gas outlet of the fuel gas separator. The method includes receiving data indicative of a parameter of a stripping gas flow through the stripping gas flowpath or of a component in flow communication with the stripping gas flow through the stripping gas flowpath; and determining an operability condition of the fuel oxygen reduction unit, or a component operable with the fuel oxygen reduction unit, based on the data received indicative of the parameter of the stripping gas flow or of the component in flow communication with the stripping gas flow.

Abstract: A fuel oxygen conversion unit includes a stripping gas flowpath for a vehicle or an engine of the vehicle. The fuel oxygen conversion unit includes a stripping gas boost pump positioned in airflow communication with the stripping gas flowpath for increasing a pressure of a flow of stripping gas through the stripping gas flowpath; a contactor defining a stripping gas inlet in airflow communication with the stripping gas flowpath, a liquid fuel inlet, and a fuel/gas mixture outlet; a fuel gas separator defining a fuel/gas mixture inlet in fluid communication with the fuel/gas mixture outlet of the contactor, a stripping gas outlet, and a liquid fuel outlet; and a connection assembly mechanically coupling the stripping gas boost pump to the fuel gas separator, the connection assembly having a speed change mechanism such that the stripping gas boost pump rotates at a different rotational speed than the fuel gas separator.

Abstract: A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet; and a fuel gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor and an axis. The fuel gas separator further includes a stationary casing; and a separator assembly including a core and a plurality of paddles extending from the core, the separator assembly rotatable about the axis within the stationary casing to separate a fuel/gas mixture received through the fuel/gas mixture inlet into a liquid fuel flow and stripping gas flow.

Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

Abstract: In one an exemplary aspect of the present disclosure, an engine includes a drive shaft; an electric machine including a stator assembly and a rotor assembly, the rotor assembly rotatable relative to the stator assembly; and an electrical break, the drive shaft coupled to the rotor assembly through the electrical break.

Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.

Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.