Abstract: A rotor assembly for an electric machine includes a cylindrical rotor core, a set of posts extending radially outward from the rotor core defining a set of slots between adjacent posts, a set of windings formed by conductive wire wound in the set of slots having end turns extending axially beyond the rotor core, and a retention case overlying the end turns.

Abstract: A crimp pin electrical connector comprising a shell defining an interior with a first and a second opening, a flange circumscribing the shell, an insert located within the interior and extending through the first opening. The insert comprising at least one crimp pin including a crimp and a pin provided within at least one passage included within the interior of the shell.

Abstract: An apparatus and method for a generator for generating power having a rotary union between a rotor and a stator, the rotary union comprising a first fluid passage having a converging nozzle and located within the stator having a first inlet and a first outlet, a second fluid passage having a diverging nozzle and located within the rotor and having a second inlet and a second outlet, the second inlet is aligned with the first outlet and at least one gap located between the rotor and stator.

Abstract: A rotor assembly for an electric machine includes a cylindrical rotor core, a set of posts extending radially outward from the rotor core defining a set of slots between adjacent posts, a set of windings formed by conductive wire wound in the set of slots having end turns extending axially beyond the rotor core, and a retention case overlying the end turns.

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: An apparatus and method for a generator for generating power having a rotary union between a rotor and a stator, the rotary union comprising a first fluid passage having a converging nozzle and located within the stator having a first inlet and a first outlet, a second fluid passage having a diverging nozzle and located within the rotor and having a second inlet and a second outlet, the second inlet is aligned with the first outlet and at least one gap located between the rotor and stator.

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 generator includes a housing, a rotor within the housing and rotatable about an axis of rotation, and a coolant sump within the housing and arranged axially parallel with the axis of rotation, wherein an aeroline of the generator can at least partially limit an aeroline of an engine cowling.

Abstract: A generator includes a housing, a rotor within the housing and rotatable about an axis of rotation, and a coolant sump within the housing and arranged axially parallel with the axis of rotation, wherein an aeroline of the generator can at least partially limit an aeroline of an engine cowling.

Abstract: A fluid supply assembly having a conduit through which a fluid may be supplied. A thermal shut-off may be provided to control the supply of fluid through the conduit in response to an environmental temperature condition.

Abstract: A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.

Abstract: A turbofan engine assembly having a turbine engine and a nacelle that surrounds at least a portion of the turbine engine to define an annular bypass duct that defines a forward-to-aft bypass air flow path. The turbofan engine assembly further comprises a fixed portion and a movable portion which is movable in a direction along the bypass air flow path to an opened position that defines a thrust reversing outlet through which at least a portion of the bypass air flow may be directed. At least one actuator moves the movable portion to the opened position.

Abstract: A fluid supply assembly having a conduit through which a fluid may be supplied. A thermal shut-off may be provided to control the supply of fluid through the conduit in response to an environmental temperature condition.

Abstract: A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.

Abstract: An aircraft hydraulic system for operating a plurality of hydraulically-operated actuators in the aircraft having a hydraulic reservoir in which hydraulic fluid is stored, a hydraulic distribution system coupling the hydraulic reservoir to the actuators and having a main flow line coupled to the hydraulic reservoir, a hydraulic pump fluidly coupled to the main flow line and the hydraulic reservoir to pump hydraulic fluid from the reservoir to the main flow line, a main filtration system fluidly coupled to the main flow line upstream of at least some of the actuators, and a self-cleaning filter fluidly coupled upstream of the main filtration system.

Abstract: A system is provided for reducing ice mass on an aircraft engine. A compressor inlet temperature and pressure sensor measures total temperature and total pressure at the inlet to the engine compressor. An ice shield is provided, wherein a plurality of wedge portions has multiple protrusions for promoting ice formation in multiple locations. The ice shield is separable from the sensor with which it interfaces. The ice shield comprises straight angle wedge shapes and curved surfaces to separate and minimize ice accretion in desired locations. The mass of each resultant ice formation is reduced to a size that the compressor inlet blades can withstand without deformation.

Abstract: The invention concerns a system for controlling an aircraft propeller. A hydraulic motor controls pitch of the propeller blades. The propeller blades are characterized by the absence of feather-inducing counterweights. An overspeed governor senses when propeller speed exceeds a limit, and, in response, assumes control of the hydraulic motor and drives the blades toward a coarsened pitch position, which reduces the propeller speed. In another form of the invention, a mechanical brake can override the hydraulic motor and mechanically retard a rotating gear, which causes the propeller blades to move toward a coarsened pitch.