Abstract: A method of high fidelity modeling an electrical power system of an aircraft, includes among other things, identifying electrical, mechanical, thermal, and EMI characteristics of the electrical power system; applying at least one circuit-based solver to model to at least one of the electrical characteristics; and applying, simultaneously with the circuit-based solver and in real-time, a field-based solver to model the remaining electrical, mechanical, thermal, and EMI characteristics.

Abstract: An electric machine having a rectifier assembly placed within a rotating shaft of the electric machine to convert the AC output of the electric machine to DC prior to transmission of the electricity from the electric machine.

Abstract: A turbofan engine includes a turbine engine having a rotatable fan and a generator. The generator further includes a main machine, an exciter, and a generator control unit for controlling the excitation of the main machine. A rotor assembly is located within one of the blades, and a stator assembly that is along a rotational path of the rotor assembly whereby the operation of the turbine engine rotates the fan, which rotates the rotor assembly along its rotational path past the stator assembly to generate electricity.

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 rotor assembly for an electric machine includes a core having at least one post and a cap wherein electrical windings are wound about the rotor assembly to define a pole. The rotation of the rotor and rotor pole relative to a stator generates a current supplied from the electric machine to a power consuming device.

Abstract: An electrical machine includes a rotor, a stator having a slot liner including an electrical insulator which extends beyond the stator ends, and a strengthening element provided at each of the slot liner ends, wherein the strengthening strip reduces the splitting of the corresponding slot liner end.

Abstract: A method for starting an electric motor, the motor having a main machine, exciter, and permanent magnet generator (PMG), each having a stator and a rotor, with each rotor mounted to a common shaft, the method comprising starting the main machine in an asynchronous mode by applying a starting current to the stator of the main machine to induce a damper current in a damper winding of the main rotor to generate a starting torque that initiates the rotation of the common shaft, and then running the main machine in synchronous mode by supplying running current from the exciter rotor to the main machine rotor.

Abstract: An electric machine having a rectifier assembly placed within a rotating shaft of the electric machine to convert the AC output of the electric machine to DC prior to transmission of the electricity from the electric machine.

Abstract: A method, system and computer program product for monitoring health of a synchronous machine is provided. The method includes receiving a plurality of phase voltage values and a plurality of phase current values. The method then computes a negative sequence voltage (Vn) based on the plurality of phase voltage values. The method also computes one or more operating parameters based on at least one of the plurality of phase voltage values and the plurality of phase current values. The method retrieves from a data store, one or more known Vn based on the one or more operating parameters. The method then computes a machine health indicator based on the computed Vn and the one or more known Vn, and raises an alarm based on the machine health indicator.

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: A generator, such as for a gas turbine engine, includes an integrated auto transformer unit having secondary windings connected to a main windings.

Abstract: A method for starting an electric motor, the motor having a main machine, exciter, and permanent magnet generator (PMG), each having a stator and a rotor, with each rotor mounted to a common shaft, the method comprising starting the main machine in an asynchronous mode by applying a starting current to the stator of the main machine to induce a damper current in a damper winding of the main rotor to generate a starting torque that initiates the rotation of the common shaft, and then running the main machine in synchronous mode by supplying running current from the exciter rotor to the main machine rotor.

Abstract: A method of high fidelity modeling an electrical power system of an aircraft, includes among other things, identifying electrical, mechanical, thermal, and EMI characteristics of the electrical power system; applying at least one circuit-based solver to model to at least one of the electrical characteristics; and applying, simultaneously with the circuit-based solver and in real-time, a field-based solver to model the remaining electrical, mechanical, thermal, and EMI characteristics.

Abstract: An assembly for a gas turbine engine includes a S/G having a rotatable shaft, a main machine, a PMG, and an exciter wherein at least one of the main machine, PMG, and exciter includes a rotor mounted to the shaft and having multiple rotor poles, a stator having multiple stator poles and at least one of the rotor poles and stator poles being formed by a core with a post and wire wound about the post to form a winding, with the winding having at least one end turn, and a layer to increase cooling capabilities of a portion of at least one of the stator and the rotor.

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: A generator, such as for a gas turbine engine, includes an integrated auto transformer unit having secondary windings connected to a main windings.

Abstract: A high-speed sleeveless rotor for an electric machine is provided. The rotor includes a shaft rotatable about a longitudinal axis, and a rotor core circumscribing at least a portion of the shaft wherein the rotor core includes an axially oriented slot. The slot includes a radially outer slot opening, a radially inner slot floor, and a slot sidewall extending therebetween. The slot floor includes a topstick attachment member extending radially outward from the slot floor and configured to engage a topstick positioned in the slot opening and the slot sidewall includes a shoulder configured to engage the topstick, preventing radially outward movement of the topstick.

Abstract: A method, system and computer program product for monitoring health of a synchronous machine is provided. The method includes receiving a plurality of phase voltage values and a plurality of phase current values. The method then computes a negative sequence voltage (Vn) based on the plurality of phase voltage values. The method also computes one or more operating parameters based on at least one of the plurality of phase voltage values and the plurality of phase current values. The method retrieves from a data store, one or more known Vn based on the one or more operating parameters. The method then computes a machine health indicator based on the computed Vn and the one or more known Vn, and raises an alarm based on the machine health indicator.

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.