An electrical assembly for an aeronautical turbomachine, including an electric machine configured to be disposed in a turbomachine and comprising a stator and a rotor comprising magnets, the assembly including a short-circuit detecting means, a hot air injecting means configured to draw hot air off the turbomachine at a temperature greater than the temperature of demagnetization of the magnets of the rotor, and to inject the drawn hot air onto the magnets of said rotor when the short-circuit detecting means detects the presence of a short-circuit in the electric machine, and a cool air injecting means, configured to draw cool air off the turbomachine and to inject it into an inner chamber of the turbomachine, the temperature of the cool air drawn by the cool air injecting means being less than the temperature of the hot air drawn by the hot air injecting means.

A power source for an aircraft having a gas turbine engine, including: an electrical connection assembly; a fuel cell assembly integrated into the gas turbine engine, electrically coupled to the connection assembly and configured to provide a first power output; and an electric machine coupled to the gas turbine engine, electrically coupled to the connection assembly and configured to provide a second power output, wherein both the first power output from the fuel cell assembly and the second power output from the electric machine are provided to the connection assembly during operating of the gas turbine engine and wherein the connection assembly is electrically coupled to an aircraft electrical load.

An aircraft electrical system including: a first DC power bus and a fuel cell assembly including a first fuel cell group, wherein the first fuel cell group is electrically coupled directly to the first DC power bus without a voltage converter to provide a first power output to the first DC power bus.

A gas turbine engine includes a fan and a rotor assembly. The rotor assembly includes a rotor, a plurality of magnets, and an annular retaining sleeve. The rotor includes a radially outer wall spaced apart from a central axis of the engine by an axially forward and an axially aft annular end wall. The magnets are located radially outward of the rotor and arranged on the outer wall in axial alignment with each other, the magnets being configured to move radially relative to each other and remain in contact with the outer wall in response to elastic deformation of the outer wall. The sleeve radially surrounds the magnets so as to structurally support and secure the magnets to the rotor, the sleeve being elastically deformable in the radial direction and configured to elastically deform based on the radial movement of the magnets.

Fault-tolerant electric drive systems including a machine having a rotor and a stator having coils arranged in pairs. Each coil in each pair separated by 180 degrees, a first phase (ϕA) having one of the coil pairs and a phase drive circuit connected therewith, a second phase (ϕB) having a second one of the coil pairs and a second phase drive circuit connected therewith, a third phase (ϕC) having a third one of the coil pairs and a third phase drive circuit connected therewith, and a fourth phase having a fourth one of the coil pairs and a fourth phase drive circuit connected therewith. Further included is a controller connected with the first, second, third and fourth phase drive circuits to control operation thereof.

An electrical power generation system including a micro-turbine alternator including a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor located aft of the first stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first and second stage compressor. An electric generator is disposed along the one or more shafts such that electrical power is generated via rotation of the one or more shafts. The electric generator is disposed along the one or more shafts between the first and second stage compressors.

An aircraft with an electrical network including electrical subnetworks; a turbo generator including a gas turbine, an electricity generator with permanent magnets having phase groups respectively connected to the electrical subnetworks, and, for each phase group, an isolation device; and a control device designed to detect a short circuit in at least one of the phase groups, each phase group in which a short circuit is detected being described as defective and each other phase group being described as healthy and, in response to the detection of the short circuit, to disconnect this defective phase group from its associated electrical subnetwork and to command the shutdown of the gas turbine. The control device is also designed, in response to the detection of the short circuit, to keep each healthy phase group connected to its electrical subnetwork.

A supercritical CO2 turbo-generator system includes multiple turbine generator units, a direct current bus, a plurality of active rectifiers, and a voltage controller. Each turbine generator unit includes a turbine with a supercritical CO2 input and a supercritical CO2 output, a generator with an electrical input and power output, a shaft connecting the turbine and generator, and a speed sensor for sensing shaft speed. The turbine generator units are connected in a cascading series with the input of a first turbine generator unit connected to a heated supercritical CO2 source and the input of each subsequent turbine generator unit is connected to the output of a prior turbine generator unit. The voltage controller monitors the speed sensor of the turbine generator units and varies the load on each generator to control shaft speed. Each active rectifier converts the power output of a generator to direct current, and the power from multiple active rectifiers is combined by the direct current bus.

A rotor assembly for a turbomachine having a permanent magnet electric motor that defines an axis of rotation includes a jacket member. The rotor assembly also includes a magnet member that is received within the jacket member. The magnet member has a first longitudinal end and a second longitudinal end that are separated along the axis of rotation. The rotor assembly also includes a first shaft structure that is attached to the first longitudinal end and a second shaft structure that is attached to the second longitudinal end. The magnet member is solitary and unitary and has a solid core

Gas turbine engines and methods of starting gas turbine engines, the gas turbine engine including: an electronic engine controller; one or more spools designated a starting spool for starting the engine, and has a required starting torque τs; a permanent magnet alternator mechanically coupled with the starting spool, the alternator, in a motor mode, provides a peak torque of τa, and, in a generator mode, generates electrical power for the electronic engine controller; and an electrical starter-generator mechanically coupled with the starting spool. The starter-generator in a motor mode, provides a peak torque of τsg, and, in a generator mode, generates electrical power for an external load. τsg+τa≥τs and τsg, τa<τs, and the electronic engine controller, during a start procedure, operates both the permanent magnet alternator and the starter-generator in a motor mode to drive the starting spool.