A power conversion system (200A) incorporated in a flight vehicle includes a power converter (10) having a semiconductor element stored therein. An energy storage (20) is disposed above the power converter (10) in the vertical direction, the energy storage storing a solid or liquid energy source…

A hydrogen fuel system (200) including a fuel delivery assembly (202), a purge gas source (310), and a vent opening (324). The fuel delivery assembly (202) is configured to receive hydrogen fuel from a hydrogen fuel source (210) and to provide the hydrogen fuel from the hydrogen fuel source (210)…

The invention concerns a turbofan engine (100) with a nacelle (102) delimiting a duct (204) and comprising a movable cowl (216) translating between advanced and retracted positions where a window (220) is open between the duct (204) and the outside, transmission systems (223), where each has at…

L'invention concerne un système de boîtier (220) monté entre une électrovanne amont (122a) d'une canalisation amont (116a) et une électrovanne aval (122b) d'une canalisation aval (116b) et comportant un boîtier (222) divisé par une paroi de séparation (234) en un premier volume (230a) mis au vide…

An aircraft power system (100) comprises a turbocharger (104), the turbocharger (104) including a compressor (108) for supplying combustion air to an internal combustion engine (102), a turbine (110) operatively connected to an internal combustion engine (102) to receive an exhaust flow from the…

The present invention relates to an aircraft (1) provided with a power plant (10) provided with at least one combustion engine (20) mechanically connected to a drive system (30), the drive system (30) comprising two electrical machines (35, 40) each connected by a kinematic chain (50) to the…

A hybrid propulsion system (50) for an aircraft (10) can include a propulsor assembly (56) having at least one propulsor (242) and a power generation system (50). The power generation system (50) can include a first power assembly (52), a second power assembly (52), a first electric machine (62)…

A balancing system (100) and method for an engine (102) of an aircraft (104) includes a housing (110) retaining a magnetorheological fluid (112) including magnetic particles (116) within a carrier fluid (114). Electromagnets are coupled to the housing (110). The electromagnets are associated with…

A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine. The propulsion system further includes, but is not limited to, an outer cover associated with the engine. The engine and the outer cover are configured for coupling to the…

Electrical systems 201 for connecting rotary electric machines 111, 113 with gas turbine spools are provided. One such electrical system 201 comprises: a first rotary electric machine 111 mechanically coupled with a first gas turbine spool and a second rotary electric machine 113 mechanically…

An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple…

A control system (34) for an aircraft hybrid propulsion system (5). The hybrid propulsion system (5) comprises a gas turbine engine (10) coupled to an electric generator (28, 32), a propulsor (12) coupled to an electric motor (28), and an electrical storage device (30) coupled to the motor (28) and…

The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (), and a thermal drive system (), including a first thermal engine (A) and a second thermal engine (B), which is configured to allow the vaned propulsion system () to be driven. The powertrain…

A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid…

A hybrid propulsion system for a vertical take-off and landing aircraft comprising at least one combustion engine driving an electricity generator, at least one electrical energy storage assembly associated with each electricity generator and defining, with each electricity generator, an energy…

A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the…

An aircraft power plant has: an electric motor; a compressor; a combustion engine; an output shaft drivingly engageable to a thrust generator for propelling an aircraft equipped with the aircraft power plant; and a transmission including a gearbox having a first input drivingly engaged by the…

Series hybrid propulsion unit including a gas turbine driving a mechanical shaft of an electric generator having n output phases and supplying an AC busbar, and a system for monitoring the speed of the gas turbine, the AC busbar supplying a plurality of AC distribution channels each composed of an…

A turbofan or turbojet arrangement for vehicles, craft, aircraft and the like, that comprises the installation of two or more gas turbines, mini-turbines, micro-turbines or nanoturbines grouped in parallel to form a single gondola and allowing for different configurations, to form a large, single…

The present invention relates to a variable cycle boost propulsor system 10 for use on an aircraft. The variable cycle boost propulsor system 10 includes an engine 14, a turbine 30, a fan 34 connected to the turbine 30, and a valve system 46 for delivering the fluid output from the engine 14 to the…