GE AVIATION SYSTEMS LLC

An electrical machine can include a rotor core rotatably coupled to a shaft, and having a set of rotor windings including a termination end extending axially out the core and electrically connected to a terminal. A lead restraint assembly is arranged to rotatably restrain the termination end in a channel.

A rotor assembly includes a rotor core having a rotatable shaft and defining at least one rotor post, a winding wound around the post that defines an end turn, and a winding support assembly including a winding support assembly coupled to the rotatable shaft. The end turn defines a set of channels therethrough and is disposed in a first chamber defined by the winding support assembly.

An electrical machine comprising a rotatable shaft; an induction generator mechanically coupled to the rotatable shaft and defining a power output connectable with an electrical load, wherein the power output defines a desired constant voltage output; a converter electrically connected with the power output; and a controller connected to the converter, the controller configured to at least one of provide supplemental power at the power output or absorb excess power at the power output.

A rotor assembly for an electric machine includes a first end and a second end, the second end distal from the first end in an axial direction, a first radial wall extending between the first end and the second end and defining an inner cavity, and a second radial wall extending between the first end and the second end, the second radial wall radially-overlying the first radial wall and defining an outer cavity between the first radial wall and the second radial wall.

A power distribution system for an aircraft, and method of operating includes, including determining, by a supplemental electrical power system, an operating mode of the aircraft, selecting, by the supplemental electrical power system, at least one supplementary power source of a set of at least two supplementary power sources, and based on the operating mode of the aircraft at least one of receiving, by the selected at least one supplementary power source, a first current from the primary power bus, or selectively providing a second current to the primary power bus from the selected at least one supplementary power source.

A method of cooling rotor winding end turns extending from a rotor core includes coupling a collar to a rotatable shaft of the rotor core. The collar has a first wall confronting the rotor core, a second wall spaced from and opposing the first wall, a third wall between the first and second walls defining a set of apertures therethrough, a first cavity cooperatively defined by the first, second and third walls, having a first opening opposing the third wall, a fourth wall circumscribing the third wall, a second cavity cooperatively defined by the second, third and fourth walls, the second cavity defining a second opening opposing the second wall. The first and second cavities are in fluid communication, and the rotor winding end turns are receivable into the second cavity. The method includes directing a coolant into the first cavity, and delivering the coolant to the second cavity.

A rotor assembly for an electric machine includes a first end and a second end, the second end distal from the first end in an axial direction, a first radial wall extending between the first end and the second end and defining an inner cavity, and a second radial wall extending between the first end and the second end, the second radial wall radially-overlying the first radial wall and defining an outer cavity between the first radial wall and the second radial wall.

An electric winding assembly includes a conductor core having a first end and an opposing second end, an insulation layer overlying the conductor core, and a conductive shield layer overlying the insulation layer. The conductive shield layer includes an insulative carrier circumferentially surrounding the insulation layer and a conductive layer disposed on the insulative carrier, the insulative carrier formed from a material having a thermal rating greater than 180° C., the conductive shield layer having a surface resistivity between 1.5 and 10 ohms per square.

A method of cooling rotor winding end turns extending from a rotor core includes coupling a collar to a rotatable shaft of the rotor core. The collar has a first wall confronting the rotor core, a second wall spaced from and opposing the first wall, a third wall between the first and second walls defining a set of apertures therethrough, a first cavity cooperatively defined by the first, second and third walls, having a first opening opposing the third wall, a fourth wall circumscribing the third wall, a second cavity cooperatively defined by the second, third and fourth walls, the second cavity defining a second opening opposing the second wall. The first and second cavities are in fluid communication, and the rotor winding end turns are receivable into the second cavity. The method includes directing a coolant into the first cavity, and delivering the coolant to the second cavity.

A power overlay module assembly that provides for or meets a desired power demand. The power overlay module assembly comprises power overlay tiles, a base, a direct current (DC) input bus bar, and an alternating current (AC) bus bar. The power overlay tiles have an arrangement of power switching components. The base receives the power overlay tiles. The DC input bus bar is electrically coupled to the power overlay tiles. The AC output bus bar comprises a non-conductive surface layer. The non-conductive surface layer insulates the AC output bus bar from the DC input bus bar, and the AC output bus bar is electrically coupled to the power overlay tiles.