In one an exemplary aspect of the present disclosure, an engine includes a drive shaft; an electric machine including a stator assembly and a rotor assembly, the rotor assembly rotatable relative to the stator assembly; and an electrical break, the drive shaft coupled to the rotor assembly through the electrical break.

A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

A gas turbine engine comprises a gearbox including a first epicyclic gearbox and a second epicyclic gearbox. The first epicyclic gearbox comprises a first sun gear meshing with the first planet gears and the first planet gears meshing with a first annulus gear. The second epicyclic gearbox comprises a second sun gear meshing with the second planet gears and the second planet gears meshing with a second annulus gear. An input shaft is arranged to drive the first sun gear and a first planet gear carrier is arranged to drive a propulsor. The first and second annulus gears are fixed to a static structure. A first clutch is arranged between the first planet gear carrier and the second planet gear carrier and a second clutch is arranged between the second sun gear and the input shaft. The gearbox is more efficient at cruise conditions.

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 turbine (10) configured to operate in a thermodynamic cycle comprising a working fluid circuit, wherein the turbine comprises an impeller (11) mounted on a first end (20a) of a turbine shaft (20), the impeller being arranged in a housing (12) with a turbine inlet (10a) for the working fluid, wherein a second end (20b) of the turbine shaft is connectable to a shaft of a generator (60) by means of a magnetic coupling (40) for transferring torque from the turbine shaft to the generator shaft, wherein a fluid tight barrier (50) is mounted on the turbine, covering the turbine shaft to seal the turbine from the surroundings, wherein the turbine further comprises at least one fluid bearing (30a, 30b, 30c) arranged on the turbine shaft and in fluid communication with the working fluid circuit to receive working fluid therefrom.

A containment shell for a magnetic pump, the shell comprising: a body section having a continuous side wall defining a chamber, and an end wall closing the chamber at one end, the chamber being open at the other end, wherein the body section and the end wall are integrally formed from a matrix material in which chopped carbon fibre material is distributed.

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.

A control valve for a fluid flow includes: a valve body that defines an inlet and an outlet for the fluid, an obstructer inserted in the valve body, and an actuator system configured for reversibly translating the obstructer between a first position, in which the obstructer allows the passage of the fluid between the inlet and the outlet, and a second position, in which the obstructer prevents the passage of the fluid between the inlet and the outlet; the control valve further includes a turbine rotor housed inside the valve body, wherein the rotor includes a plurality of blades and is configured for continuously rotating under the action of the fluid flowing between the inlet and the outlet, the rotor rotating about an axis of rotation substantially aligned with the direction of translation of the obstructer.

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine via a decoupler.

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.