A turbocharger includes a compressor configured to compress intake air for an engine. The turbocharger further includes an electric motor configured to power the compressor. The turbocharger further includes a turbine configured to receive exhaust air from the engine. The turbocharger further includes an electric generator configured to be driven by the turbine to generate electric power.

A system for hybrid propulsion for an aircraft includes a gas turbine engine having a power shaft. A motor generator is operatively connected to the power shaft of the gas turbine engine and configured to produce electric power. An electric propulsion motor is configured to receive the electric power and be selectively driven at an operational speed independent of a rotational speed of the power shaft.

A gas turbine engine comprises an electronic control unit adapted to control functions of the gas turbine engine and having a DC power input unit coupled to receive DC supply power and an ignition igniter coupled thereto. The ignition exciter includes an AC power input unit adapted to receive AC power from an AC power source within the gas turbine engine, a power rectification unit coupled to receive the AC power from the AC power source and configured, upon receipt thereof, to rectify the AC power into DC power, and a DC power output unit coupled to receive the DC power from the power rectification unit and configured to supply the DC power to the DC power input unit of the electronic control unit as DC supply power and/or the ignition igniter.

A motor arrangement includes a shaft, a motor with a cage winding fixed in rotation relative to the shaft, and a generator. The generator includes a permanent magnet assembly fixed in rotation relative to the shaft. The permanent magnet assembly and the cage winding are fixed in rotation relative to one another such that the generator generates a sinusoidal AC voltage signal according to an excitation phase applied to the motor for controlling rotor distortion during cool down of a gas turbine engine.

A method, including receiving a turbine system operating parameter. The turbine system operating parameter includes an indication of a frequency variation of an electric power system associated with the turbine system. The method includes determining a correction factor to vary the output of the turbine system according to the frequency variation, wherein the correction factor is based on a droop power response and a nominal droop power ratio. The droop power response is calculated based on a gas turbine power output and a speed-load error. The method further includes varying the output of the turbine system based at least in part on the correction factor.

The invention concerns land-based gas turbine plants with a multi-spool gas turbine arrangement for generating electrical power to supply a load (200). The invention comprises at least three spools (10a-10c). Each of the at least three spools (10a-10c) comprises a shaft (11a-11c), a compressor (C1-C3) and a turbine (T1-T3). Each one of the shafts (11a-11c) of the at least three spools (10a-10c) are independently rotatable with respect to each other. The invention further comprises electrical generators (G1-G3) mounted on each of the shafts (11a-11c) of the at least three spools (10a-10c), the output power of the generators being independently controllable and at least 60 percent of a total output power supplied to said load (200) in a form of electrical and rotational power is generated by the at least three generators (G1-G3) in the form of electrical energy.

The invention concerns land-based gas turbine plants with a two-spool gas turbine arrangement for generating electrical power. The invention comprises two spools. The first spool comprises a first shaft, a first compressor and a first turbine. The second spool comprises at least a second shaft and a second turbine. The shafts of the first and the second spools are independently rotatable of each other. The invention further comprises the first generator and the second generator having nominally substantially equal power ratings, and the rotating parts of the first generator and the second generator have nominally substantially equal rotational speed ratings, and at least 60 percent of a total output power supplied to said load in a form of electrical and rotational power is generated by the two electrical generators.

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 starter/generator. A main bridge gate driver is configured to drive a MOSFET-based bridge during start mode using Space Vector Pulse Width Modulation (SVPWM) and during generate mode using reverse conduction based inactive rectification.

A drive system for driving a load, comprising a gas turbine configured and arranged for driving the load, an electric motor/generator electrically connected to an electric power grid, a first load coupling connecting the gas turbine to the load, a second load coupling, connecting the load to the electric motor/generator. The electric motor/generator is adapted to function as a generator for converting excess mechanical power from the gas turbine into electrical power and delivering the electrical power to the electric power grid, and as a motor for supplementing driving power to the load. The drive system comprises furthermore a disconnecting device to reversibly disconnect the load from the gas turbine, so that the load can be driven only by the motor.

A start inverter for an electric engine start scheme includes an inverter phase leg with solid-state switches and a pulse width modulator operatively connected to the solid-state switches of the inverter phase leg. The pulse width modulator provides command signals to the solid-state switches of the inverter phase leg to invert direct current into alternating current with less ripple than a start inverter with two solid-state switches per phase leg.