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.

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.

A gas turbine engine including a compressor has a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine includes a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. The first shaft includes at least one magnetic section. An electromagnet is disposed radially outward of the first shaft at an axial location of the at least one magnetic section, relative to an axis defined by the gas turbine engine.

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 gas turbine engine, in particular for an airplane, includes a bladed rotor, a shaft driven by a turbine and an electrical generator including first and second generator components that can be rotated and magnetically coupled to one another, the first one being fixed to the shaft and the second one being mechanically coupled to the bladed rotor so as to drive the bladed rotor.

A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing.

An electrical power generation system includes a micro turbo alternator having combustion chamber, a turbine driven by combustion gases from the combustion chamber and a compressor operably connected to the combustion chamber to provide a compressed airflow thereto. A permanent magnet generator is located along a shaft connecting the compressor and turbine such that electrical power is generated via rotation of the shaft, and a cyclonic dirt separator operably connected to a compressor inlet. The cyclonic dirt separator includes an air inlet, and an air exhaust disposed at opposing ends of a housing. The cyclonic dirt separator is configured to induce circumferential rotation into the airflow entering through the air inlet, and separate the airflow into a clean airflow and a relatively dirty airflow, such that the relatively dirty airflow flows through the air exhaust and the clean airflow is directed to the compressor inlet.

Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.

The present invention is directed to a direct-drive fan system and a variable process control system for efficiently managing the operation of fans in a cooling system such as a wet-cooling tower or air-cooled heat exchanger (ACHE), HVAC systems, mechanical towers or chiller systems. The present invention is based on the integration of key features and characteristics such as tower thermal performance, fan speed and airflow, motor torque, fan pitch, fan speed, fan aerodynamic properties, and pump flow. The variable process control system processes feedback signals from multiple locations in order control a high torque, variable speed, permanent magnet motor to drive the fan. Such feedback signals represent certain operating conditions including motor temperature, basin temperature, vibrations, and pump flow rates. Other data processed by the variable process control system in order to control the motor include turbine back pressure set-point, condenser temperature set-point and plant part-load setting. The variable process control system processes this data and the aforesaid feedback signals to optimize the operation of the cooling system in order to prevent disruption of the industrial process and prevent equipment (turbine) failure or trip. The variable process control system alerts the operators for the need to conduct maintenance actions to remedy deficient operating conditions such as condenser fouling. The variable process control system increases cooling for cracking crude and also adjusts the motor RPM, and hence the fan RPM, accordingly during plant part-load conditions in order to save energy.

An electric machine (212) comprises a turbomachine rotor (203) having a hub (302) and an axis of rotation (A-A) about which the turbomachine rotor is arranged to rotate. The turbomachine rotor includes a plurality of blades (301). Each blade has a root (303) attached to the hub, a tip (304) remote from the hub, a leading edge (305) and a trailing edge (306), a pressure side and a suction side (307). A stator (502) is located circumferentially around the turbomachine rotor. Each blade further comprises a rotor element at the tip comprising a permanent magnet having a first pole (401) and a second pole (402), the first pole being located adjacent the suction side of the blade and the second pole being located adjacent the pressure side such that a magnetic flux path extends perpendicularly through the blade tip.