An electrical generator, comprising a rotatable impeller locatable within a flow path of a conduit. The impeller is rotated by fluid flowing along said flow path. The impeller comprises a magnetic portion, the generator further including a stator located external of the flow path. The stator generating electrical power in response to rotation of the magnetic portion.

An aircraft starting and generating system includes a starter/generator that includes a main machine, an exciter, and a permanent magnet generator. The system also includes an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the. A load-leveling unit (LLU) is selectively coupled with a DC power output from the starter/generator and has an inverter/converter/controller (ICC) with an LLU metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration that supplies DC power to the DC power output in a supply mode, and that receives DC power from the DC power output, in a receive mode. A LLU bridge gate driver is configured to drive the LLU MOSFET-based bridge during a supply mode and a receive mode using bi-polar pulse width modulation (PWM).

An embedded turbofan deicer system (ETDS) may eliminate the ingested ice crystal icing problem plaguing high bypass turbofan engines operating at high altitudes near convective tropical storms: icing occurring on the surfaces of the engine's rotating engine spinner, fan blades, low pressure compressor casing and low pressure compressor and causing loss of power and on occasion engine flameouts. The invention supplies electricity to heat these engine parts using at least one reversed permanent magnet electric generator (reversed PMEG) driven by the turbofan's central drive shaft with all parts of the ETDS mounted internal to the engine in presently unused internal spaces without requiring modifications to the existing engine. All electric power produced by the rotating reversed PMEG supplied directly to rotating engine parts requiring heat for deicing. A unique method to deice metal, composite and metal/composite fan blades is included in the invention using electricity from the reversed PMEG.

A super-cooled propellant powered generator system which generates an amount of electrical energy and is driven by a super-cooled propellant includes first and second rotator support assemblies comprising first and second support units and guide members attached thereto, respectively. A rotator assembly includes a rotator unit disposed in a rotational relationship relative to the guide members, the rotator unit having one or more propulsion vanes mounted therein. A rotator magnet assembly includes at least a rotator magnet mounted around the rotator unit and rotational therewith. A stator assembly having a stator unit is disposed in an electrical generating orientation relative to the rotator magnet. A super-cooled propellant transmission assembly transmits super-cooled propellant to and through the support units and rotator unit into contact with the propulsion vanes thus rotating the rotator unit and rotator magnet mounted thereto relative to the stator unit, and generating the amount of electrical energy.

A power generation unit is connected with an engine rotary shaft via an accessory gearbox. A rotor extends through the accessory gearbox and a drive gear is disposed at an intermediate portion of the rotor for driving the latter. Permanent magnet elements are mounted on opposite side portions with the intermediate portion intervening therebetween, and stator coils are disposed so as to confront respective outer peripheries of the permanent magnet elements.

A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.

An aircraft fuel system includes a fuel tank, a fuel pump configured to receive a fuel flow from the fuel tank via a fuel supply line. The fuel system further includes a tap fluidly coupled to an outlet of the fuel pump, at least one generator or permanent magnet machine fluidly connected to the fuel pump via the tap, and the tap is configured to deliver fuel to the at least one generator or permanent magnet machine. The fuel system further includes a gearbox mechanically connected to the at least one generator or permanent magnet machine.

An electrical power-transfer system for an engine includes first and second engine shafts. The system also includes a planetary gear system having a sun gear, a ring gear, a plurality of planetary gears enmeshed with the sun gear and the ring gear, and a carrier supporting the plurality of planetary gears, where the carrier is configured for connection to be driven by the first engine shaft. The system further includes a first electrical machine connected to be driven by the ring gear to generate electrical power, a second electrical machine connected to drive the sun gear, and a third electrical machine configured to receive electrical power generated by the first electrical machine and operable as a motor to drive the second engine shaft.

An electrical power-transfer system for an engine includes first and second engine shafts. The system also includes a planetary gear system having a sun gear, a ring gear, a plurality of planetary gears enmeshed with the sun gear and the ring gear, and a carrier supporting the plurality of planetary gears, where the carrier is configured for connection to be driven by the first engine shaft. The system further includes a first electrical machine connected to be driven by the ring gear to generate electrical power, a second electrical machine connected to drive the sun gear, and a third electrical machine configured to receive electrical power generated by the first electrical machine and operable as a motor to drive the second engine shaft.