The present utility model discloses a modular magnetic-type fan convenient for installation, which comprises a housing, a magnetic-type structure and an electrical-connection structure; the housing is surrounded by a plurality of side frames; the magnetic-type structure comprises a first magnetic part and a second magnetic part arranged on both side frames; the electrical-connection structure comprises a first electrical-connection part and a second electrical-connection part arranged on two side frames; the users can splice fans in accordance with their actual needs make the fan combinations more convenient and avoid messy electrical connection.

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

An electrical power generation system including a micro-turbine alternator. The 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. 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 stage compressor and second stage compressor. The one or more shafts include a turbine shaft attached to the at least one turbine a compressor shaft attached to the first stage compressor, and a coupling assembly configured to operably connect the turbine shaft to the compressor shaft via a magnetic coupling force.

The present disclosure provides an electrically gear turbofan that includes a fan; a first spool shaft; and an electrical gearbox including: an armature winding connected to the first spool shaft and coupled to a power source; and a magnetic receiver connected to the fan, and wherein an air gap is defined between the armature winding and the magnetic receiver. The turbines and electrical gearing enable an operator to rotate the spool shaft at a first rotational speed; power an armature winding to generate an armature magnetic field, wherein the armature magnetic field rotates at a second rotational speed; transfer rotational energy via the armature magnetic field from the spool shaft to the magnetic receiver; and rotate the fan at a third rotational speed. In some aspects, the third rotational speed is controlled via a direction and a magnitude of the second rotational speed relative to the first rotational speed.

A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.

An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.

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.

An electrical power generation system including a micro-turbine alternator. The 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. 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 stage compressor and second stage compressor. The one or more shafts include a turbine shaft attached to the at least one turbine a compressor shaft attached to the first stage compressor, and a coupling assembly configured to operably connect the turbine shaft to the compressor shaft via a magnetic coupling force.

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 hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.