Provided is a method of assessing rotor temperature during operation of a permanent magnet synchronous machine, including a stator having at least one winding set, the method including: providing reference flux linkage values for different rotor and stator temperature values and current values of an operating winding set; measuring an actual rotor temperature value; measuring an actual stator temperature value; measuring an actual current value of an operating winding set; deriving and storing reference flux linkage values for a given set of operating conditions, in particular, by means of a reference run; deriving a reference flux linkage value (for the measured actual rotor and stator temperature values and the measured actual current value of the operating winding set) using the flux model; obtaining a voltage value; deriving an estimated flux linkage value; deriving a rotor temperature offset; and assessing the rotor temperature based on the rotor temperature offset.

An anti-ice system for a gas turbine engine may comprise a power generating device and a first thermally conductive applique comprising a first heating circuit. The power generating device may comprise a first component configured to rotate about an axis and generate a current. A first conductive layer may electrically couple the first heating circuit and the first component of the power generating device.

An aircraft electric power generation and start system (EPGSS) includes a main machine, a starter permanent magnet generator (PMG), a generator PMG, and a carrier injection sensorless (CIS) system. The main machine selectively operates in a start mode or a generator mode. The starter PMG includes a first PMG stator and a first PMG rotor and is configured to rotate along with the shaft. The generator PMG includes a second PMG stator and a second PMG rotor configured to rotate along with the shaft. The CIS system determines one or both of a PMG voltage and a PMG current corresponding to the first PMG during the start mode, and determines a rotational position of the main rotor based on one or both of the PMG voltage and the PMG current.

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.

A ram-jet and turbo-jet detonation engine includes an inlet part and a discharge part both shaped as axis-symmetrical round hollow rotating cones interconnected by a narrow middle part, having vanes, mounted on the internal surfaces of the cones, not completely overlapping a central part of a channel, and form spirals, twisted about a common central axis of the channel. The inlet cone with vanes serves as a ventilator/compressor, and the discharge cone with vanes serves as a turbine and discharge nozzle. The middle part and the discharge cone are built as one integral component. A centripetal pump supplies fuel to a mixing section. The engine includes a firing system, generating short high-voltage electrical pulses, providing for burning of combustible mixture in a detonation mode. The invention enables an independent horizontal take-off of flying apparatus and a possibility of varying/alternating the speed within a range from subsonic to hypersonic.

A power generation system includes a shroud that defines a fluid flow path. A gas turbine engine is in the fluid flow path, and the gas turbine engine includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor. An electric generator is in the fluid flow path upstream from the turbine, and the electric generator includes a rotor coaxially aligned with the turbine. A plurality of non-lubricated bearings rotatably support the gas turbine engine.

A power module includes a turbine arranged along a rotation axis, an interconnect shaft fixed in rotation relative to the turbine, and a compressor with a regenerative compressor wheel. The regenerative compressor wheel is fixed in rotation relative to the interconnect shaft supported for rotation with the turbine about the rotation axis. Generator arrangements, unmanned aerial vehicles, and methods of generating electrical power are also described.

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.

A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.

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.