Abstract: An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

Abstract: An electrical filter circuit is disclosed. The circuit includes a first input line and a second input line. A first transmission line is coupled electrically in series at a first node with a first output line, and an inductor is coupled electrically in series between the first input line and the first transmission line. The filter also includes a second transmission line having a first impedance coupled to the first node. The second input line is coupled electrically in series at a second node with a second output line. A third transmission line is coupled to the second node, and a capacitor is coupled electrically in series between the second transmission line and the third transmission line. The first output line has a second impedance that is greater than the first impedance.

Abstract: An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

Abstract: An electrical filter circuit is disclosed. The circuit includes a first input line and a second input line. A first transmission line is coupled electrically in series at a first node with a first output line, and an inductor is coupled electrically in series between the first input line and the first transmission line. The filter also includes a second transmission line having a first impedance coupled to the first node. The second input line is coupled electrically in series at a second node with a second output line. A third transmission line is coupled to the second node, and a capacitor is coupled electrically in series between the second transmission line and the third transmission line. The first output line has a second impedance that is greater than the first impedance.

Abstract: An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

Abstract: A method and apparatus for operating an overvoltage response for an electric machine includes opening a first switching element and a second switching element in response to an overvoltage condition. In the instance that the overvoltage condition persists, the method and apparatus can further open a third switchable element to cease the overvoltage condition.

Abstract: An electric generator assembly for an aircraft is provided.

Abstract: A method and apparatus for operating an overvoltage response for an electric machine includes opening a first switching element and a second switching element in response to an overvoltage condition. In the instance that the overvoltage condition persists, the method and apparatus can further open a third switchable element to cease the overvoltage condition.

Abstract: A slot liner for a rotor assembly in one embodiment includes a metallic support member and a coating. The coating is disposed on at least one side of the metallic support member, and includes a mixture of a filler and a polyimide resin. The filler is a high thermal conductivity electrical insulating (HTCEI) filler, and includes particles of at least one of boron nitride, aluminum nitride, or a diamond material.

Abstract: A method and apparatus for operating a generator control unit having power bridge, further including having an input and at least one output, wherein the input is operably coupled with a generator power output, and a controller communicatively coupled with the power bridge and configured to operate the power bridge.

Abstract: A slot liner for a rotor assembly in one embodiment includes a metallic support member and a coating. The coating is disposed on at least one side of the metallic support member, and includes a mixture of a filler and a polyimide resin. The filler is a high thermal conductivity electrical insulating (HTCEI) filler, and includes particles of at least one of boron nitride, aluminum nitride, or a diamond material.

Abstract: A constant frequency starter/generator for a turbine engine includes a first inverter/converter, a second inverter/converter, a DC link electrically connecting the first inverter/converter to the second inverter/converter, and an electric machine having a synchronous main machine, wherein the constant frequency starter/generator is operable in a start mode and a run mode.

Abstract: A constant frequency starter/generator for a turbine engine includes a first inverter/converter, a second inverter/converter, a DC link electrically connecting the first inverter/converter to the second inverter/converter, and an electric machine having a synchronous main machine, wherein the constant frequency starter/generator is operable in a start mode and a run mode.

Abstract: An apparatus for powering an aircraft by generating power from a pressure spool of a turbine engine. AC power can be extracted from the turbine engine by a generator having an integrated autotransformer unit, and converted to DC power.

Abstract: An electrical architecture for an aircraft providing power for the aircraft by generating power from a high pressure spool and a low pressure spool of a turbine engine. The spools can be used to drive corresponding generators; the power from which can be used to supply the various loads of the aircraft.

Abstract: An apparatus for powering an aircraft by generating power from a pressure spool of a turbine engine. AC power can be extracted from the turbine engine by a generator having an integrated autotransformer unit, and converted to DC power.

Abstract: An apparatus for use with a flight control actuator and method for assembling the same is provided. The apparatus includes a motor drive system and a control unit. The motor drive system includes a capacitor-based energy storage configured to store and provide energy within or proximate to the actuator. The control unit is coupled to the motor drive system and is configured to facilitate managing power within or proximate to the actuator.

Abstract: A method is provided for using a temporary power source to transfer a power bus from a first power source to a second power source. The first power source operates at a first electrical frequency, and the second power source operates at a second electrical frequency that is different from the first electrical frequency. The method includes adjusting the output frequency of the temporary power source to match the first electrical frequency and supplying power to the power bus from the temporary power source. The method also includes disconnecting the first power source from the power bus. The method further includes adjusting the output frequency of the temporary power source to match the second electrical frequency. The method further includes coupling the second power source to the power bus.

Abstract: A starting and generating system for use with an aircraft engine includes a starter/generator and an inverter/converter/controller (ICC) coupled to the starter/generator. The starter/generator is configured to start the aircraft engine in a start mode and to generate AC power in a generate mode. The starter/generator includes an exciter and a rotational shaft. The ICC is configured to provide AC power at a first frequency the starter/generator in the start mode and to control the exciter during the generate mode such that the generate mode AC power has a second frequency, wherein the first frequency is based on a shaft speed of the shaft.

Abstract: A bus centering device for use in an aircraft electrical power distribution system that includes a positive bus rail, a negative bus rail, and a ground is described. The device includes a central node, a first and second switching component configured to couple the central node to the positive rail and the negative rail for a first and second predetermined duty cycle, respectively. The device includes an inductive component coupled between the central node and ground, and is configured to maintain a voltage at the central node substantially equal to ground, wherein a voltage between the positive rail and the central node is maintained substantially equal to a voltage between the negative rail and the central node. The device includes a first and second current limiting device configured to maintain a continuity of current from the inductive component when the first and second switching components are turned off.