Abstract: Hybrid electric propulsion systems and methods therefore are provided. More particularly, the present disclosure is directed to control systems for hybrid electric propulsion systems for aerial vehicles that are configured for rapidly and automatically taking action in response to rapid electrical load changes on a torque source, such as an engine. Methods for operating hybrid electric propulsion systems for aerial vehicles are also provided.

Abstract: A method for operating a permanent magnet electric machine of an engine includes determining a fault condition of the permanent magnet electric machine; and reducing a magnetism of one or more permanent magnets of the permanent magnet electric machine by increasing a temperature of the one or more permanent magnets in response to determining the fault condition of the permanent magnet electric machine.

Abstract: A system for providing mechanical and electrical power in a vehicle or other engine-driven platform includes a first engine having a first power rating and a second engine having a second power rating that is less than the first power rating. The system further includes a first generator (for example, an alternator) for generating electrical power for a load operation (such as vehicle propulsion), and a second generator (for example, a DFIG) for generating fixed frequency electrical power; both generators are operatively connected to and powered by the first and/or second engines. The first and/or second engines may be selected to power the first generator for generating power for vehicle propulsion or another load operation depending upon situational power requirements of the engine-driven platform.

Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.

Abstract: An electric machine includes a stator assembly including a first stator segment and a second stator segment, the first and second stator segments each including a plurality of laminations extending generally along a circumferential direction, each pair of adjacent laminations of the first and second stator segments defining a gap therebetween. The first and second stator segments are assembled together such that the laminations of the first stator segment are arranged at least partially in the gaps between the laminations of the second stator segment.

Abstract: An axial flux electric machine includes a rotor assembly rotatable about an axis, and a stator assembly. The stator assembly includes a stator face defining an air gap along an axial direction with the rotor assembly, the stator assembly further including a yoke, the yoke including a back surface, the back surface defining an inwardly sloped angle with the radial direction greater than two degrees.

Abstract: A multi-energy storage device system includes an electric drive coupled to a load, a DC link coupled to the electric drive, and a bi-directional voltage converter having an output channel coupled to the DC link and an input channel. A first energy storage device (ESD) is coupled to the input channel, and a switch is coupled to the DC link and to a second ESD. A system controller causes the switch to couple the second ESD to the DC link for delivering energy stored in the second ESD to the electric drive. The system controller also causes the voltage converter to convert a voltage of the first ESD to a higher voltage and to deliver the higher voltage to the DC link, wherein the higher voltage is greater than the voltage of the second ESD and causes the switch to decouple the second ESD from the DC link.

Abstract: An apparatus and method of operating a set of generators supplying power to a common power bus, includes obtaining a first generator speed signal and a second generator speed signal, determining a common mode torsional oscillation value and a differential mode torsional oscillation value, determining a first generator share command and a second generator share command based on the common mode torsional oscillation value and the differential mode torsional oscillation value, and applying the first and second generator share commands.

Abstract: An apparatus and method of operating a set of generators supplying power to a common power bus, includes obtaining a first generator speed signal and a second generator speed signal, determining a common mode torsional oscillation value and a differential mode torsional oscillation value, determining a first generator share command and a second generator share command based on the common mode torsional oscillation value and the differential mode torsional oscillation value, and applying the first and second generator share commands.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and positioned against the rotor flange. The electric machine includes a stator assembly including a tracking tooth in magnetic flux communication with the rotor magnets across an air gap. The stator assembly further includes an actuator operable with the tracking tooth to move the tracking tooth along the radial direction to adjust a height of the air gap.

Abstract: A propulsion system for an aircraft includes an electric generator mechanically driven by a combustion engine, with the electric generator configured to generate alternating current electrical power. The propulsion system additionally includes a power bus electrically connected to the electric generator and configured to receive and transmit the alternating current electrical power generated by the electric generator. Additionally, the propulsion system includes, an electric propulsor assembly comprising an electric motor and a propulsor drivingly connected to the electric motor, the electric motor electrically coupled to the power bus for the receiving alternating current electrical power from the power bus.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole p = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole P = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: An apparatus and method for a generator assembly for a drive train such as a rotatable turbine engine assembly. The generator assembly includes at least first and second generators mechanically coupled to the drive train. First and second dampers are operably coupled to the first and second generators, respectively, to selectively damp the first and second generators. Damping the first and second generators can reduce or eliminate both common mode and differential mode torsional oscillations from the generators to the drive train.

Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.

Abstract: One example aspect of the present disclosure is directed to a method for operating a gas turbine engine. One example aspect of the present disclosure is directed to a method for operating a gas turbine engine, the gas turbine engine including at least a high pressure spool and a low pressure spool. The method includes causing, by one or more control devices, electrical power to be drawn from the high pressure spool and the low pressure spool into a power distribution system. The method includes determining, by the one or more control devices, a power adjustment event associated with the high pressure spool. The method includes initiating, by the one or more control devices, a power assist operation to redirect electrical power to the high pressure spool based at least in part on the power adjustment event.

Abstract: A system for providing mechanical and electrical power in a vehicle or other engine-driven platform includes a first engine having a first power rating and a second engine having a second power rating that is less than the first power rating. The system further includes a first generator (for example, an alternator) for generating electrical power for a load operation (such as vehicle propulsion), and a second generator (for example, a DFIG) for generating fixed frequency electrical power; both generators are operatively connected to and powered by the first and/or second engines. The first and/or second engines may be selected to power the first generator for generating power for vehicle propulsion or another load operation depending upon situational power requirements of the engine-driven platform.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and positioned against the rotor flange. The electric machine includes a stator assembly including a tracking tooth in magnetic flux communication with the rotor magnets across an air gap. The stator assembly further includes an actuator operable with the tracking tooth to move the tracking tooth along the radial direction to adjust a height of the air gap.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and a having a rotor magnet embedded within the rotor disk. The electric machine further includes a stator assembly in axial or radial magnetic flux communication with the rotor magnets to generate a torque.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and supported by the rotor flange such that the rotor flange absorbs centrifugal loads exerted on the magnets and enables high speeds of operation.