An electric power generator comprises a rotor and a plurality of stators arranged coaxially and concentrically about a central axis. There is an inner stator provided radially inwardly of the rotor separated by an inner airgap and an outer stator provided radially outwardly of the rotor separated by an outer airgap. The rotor includes a plurality of magnetic pole structures configured to provide or generate a magnetic field having plurality of magnetic poles. The rotor is not of uniform cross-sectional thickness, wherein: an inner surface of the rotor bulges inwardly at the pole structures, the inner airgap being non-uniform as it is radially shorter at the pole structures and longer in between the pole structures; and an outer surface of the rotor bulges outwardly at the pole structures, the outer airgap being non-uniform as it is radially shorter at the pole structures and longer in between the pole structures.

An actuation system includes: a generating rotating electrical machine including a first stator including at least one output stator winding; a driving rotating electrical machine including a second rotor, intended to actuate a lubrication pump, and a second stator including at least one input stator winding; an array of switches electrically connected to the at least one output stator winding and to the at least one input stator winding, for electrically connecting them together or disconnecting them from each other depending on the state of the array of switches; and a control device configured to control the array of switches, depending on the state of a control signal, in such a way as to electrically connect or not connect the at least one output stator winding and the at least one input stator winding together.

An actuation system includes: a generating rotating electrical machine including a first stator including at least one output stator winding; a driving rotating electrical machine including a second rotor, intended to actuate a lubrication pump, and a second stator including at least one input stator winding; an array of switches electrically connected to the at least one output stator winding and to the at least one input stator winding, for electrically connecting them together or disconnecting them from each other depending on the state of the array of switches; and a control device configured to control the array of switches, depending on the state of a control signal, in such a way as to electrically connect or not connect the at least one output stator winding and the at least one input stator winding together.

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive an electric motor shaft. A transmission system includes at least one gearbox. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the electric motor shaft and to convert the rotation input power to output power.

An electromagnetic transmission assembly. The electromagnetic transmission assembly includes a stator having a central axis and a plurality of selectively-energized electromagnetic poles. A first rotor assembly is rotatably supported for rotation about the central axis. The first rotor assembly including a first rotor shaft and a castellated rotor including a plurality of radially arranged ferromagnetic pole portions disposed in a housing. A second rotor assembly is rotatably supported for rotation about the central axis. The second rotor assembly includes a second rotor shaft and a permanent-magnet rotor. The first rotor assembly is at least partially magnetically coupled to the second rotor assembly when the plurality of electromagnetic poles are energized.

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.

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.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

An electrical machine system includes a stator having a conical stator surface defining a rotary axis. A rotor is operatively connected to the stator for rotation relative thereto, wherein the rotor includes a conical rotor surface. A conical gap is defined between the conical surfaces of the stator and rotor about the rotary axis. An actuator is operatively connected to at least one of the stator and rotor for relative linear motion along the rotary axis of the stator and rotor to change the conical gap, wherein the actuator provides relative linear motion between a first position for a first conical gap width and a second position for a second conical gap width different form the first conical gap width. In both the first and second positions the full axial length of one of the rotor or stator is axially within the axial length of the other.