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.

A power generation system includes a shroud that defines a fluid flow path. A compressor is in the fluid flow path, and a combustor is in the fluid flow path downstream from the compressor. A turbine is in the fluid flow path downstream from the compressor and the combustor. An electric generator is in the fluid flow path upstream from the compressor, and the electric generator includes a rotor coaxially aligned with the turbine.

A gas turbine rotor having a combination of proximal embedded permanent magnets in the blended turbine(s) trunnion structure to which blades are integral to and through these distal trunnion channels attach to which turbine blades are integral to as a single component is provided. Permanent magnets or warm conducting coils or cold superconducting coils can be used. The structure rotates around a superconducting power shaft core (SPSC), running axially in relation to the turbine blade permanent magnets, for example, and embedded distal trunnion rings.

An aircraft gas turbine engine (10) comprises a main engine shaft (22, 23), a main engine shaft bearing arrangement (36, 49, 50) configured to rotatably support the main engine shaft (22, 23), and an electric machine (30) comprising a rotor (32) and a stator (34). The rotor (32) is mounted to the main engine shaft (22, 23) and is rotatably supported by a further electric machine bearing arrangement (70, 72) extending between the rotor (34) and the stator (32), and the stator (32) is mounted to static structure (38) of the gas turbine engine (10).

Fault-tolerant four-phase electric drive systems are provided. One such system comprises: a rotary electric machine having a permanent magnet rotor and an alternate-wound stator having eight evenly-spaced coils arranged in pairs, each coil in each pair being separated by 180 degrees; a first phase (A) comprising a first one of the coil pairs and a first phase drive circuit connected therewith; a second phase (B) separated by +45 degrees from the first phase and comprising a second one of the coil pairs and a second phase drive circuit connected therewith; a third phase (C) separated by +90 degrees from the first phase and comprising a third one of the coil pairs and a third phase drive circuit connected therewith; a fourth phase (D) separated by +135 degrees from the first phase and comprising a fourth one of the coil pairs and a fourth phase drive circuit connected therewith; and a controller connected with the first, second, third and fourth phase drive circuits to control operation thereof.

The present disclosure provides an electrical generator within an engine that includes a permanent magnet that emits a first magnetic field and is disposed on a first shaft; a first winding connected to a second shaft such that the first winding is positioned within the first magnetic field; a field winding disposed on the second shaft such that the field winding generates a second magnetic field that rotates as first shaft rotates relative to the second shaft; a second winding disposed on the first shaft, the second winding being positioned to receive the second magnetic field and provide a resonant emitter with an electrical power input to generate a third magnetic field when the first shaft rotates relative to the second shaft; and a resonant receiver disposed on an enclosure of the engine, positioned to receive the third magnetic field and convert the third magnetic field into an electrical output.

A shrouded bladed-rotor for use as a rotor of an electrical generator incorporates a plurality of blades and an annular magnetically-permeable yoke concentric with an associated axis of revolution. An even-numbered plurality of permanent magnets are operatively coupled to an outer surface of the annular magnetically-permeable rotor yoke, the latter of which comprises either a shroud of the shrouded bladed-rotor or a ring of magnetically-permeable material encircling the shroud. The North-South axis of each permanent magnet is substantially radially oriented with respect to the axis of rotation, and North-South orientations of every pair of circumferentially-adjacent permanent magnets of the plurality of permanent magnets are opposite to one another. A non-magnetic magnet-retaining-ring encircling the plurality of permanent magnets has sufficient hoop strength to retain the plurality of permanent magnets on the annular magnetically-permeable rotor yoke during intended operation of the electrical generator.

The present disclosure provides an electrical generator within an engine that includes a permanent magnet that emits a first magnetic field and is disposed on a first shaft; a first winding connected to a second shaft such that the first winding is positioned within the first magnetic field; a field winding disposed on the second shaft such that the field winding generates a second magnetic field that rotates as first shaft rotates relative to the second shaft; a second winding disposed on the first shaft, the second winding being positioned to receive the second magnetic field and provide a resonant emitter with an electrical power input to generate a third magnetic field when the first shaft rotates relative to the second shaft; and a resonant receiver disposed on an enclosure of the engine, positioned to receive the third magnetic field and convert the third magnetic field into an electrical output.

Electrical power generation system for an aircraft, including: a gas turbine having a high-pressure shaft and outputting a gas flow to actuate a free turbine, a polyphase permanent magnet generator coupled to the gas turbine and able to output a first alternating voltage for supplying through first conversion means a primary power supply network of the aircraft, the free turbine and the permanent magnet generator being mounted on the same drive shaft concentric with the high-pressure shaft of the gas turbine, a starter mounted on the high-pressure shaft able to ensure the starting of the gas turbine, the starter being a permanent magnet starter/generator able to output a second alternating voltage for supplying a secondary power supply network of the aircraft and auxiliary equipment of the gas turbine and the first conversion means include two first AC/DC converters controlled from a management unit.

An electrical machine has a variable reluctance rotor, and a stator formed as an annular array of stator segments. The reluctance of the rotor-to-stator magnetic flux path varies with rotor position whereby the stator segments are magnetically energizable to rotate the rotor. The stator segments are arranged in the array such that, when energized to rotate the rotor, they produce an unbalanced force on the rotor. The machine further has a compensator including one or more balancing segments which are configured to be magnetically energizable to produce a balancing force on the rotor which balances the unbalanced force. The reluctance of the rotor-to-compensator magnetic flux path is substantially invariant with rotor position.