Safran Helicopter Engines

Safran

Loïs Pierre Denis Vive

Olivier Bedrine

Thomas Drouin

Camel Serghine

Thomas Klonowski

Laurent Pierre Tarnowski

Bernard Claude Pons

Alphonse Puerto

Jean-Maurice Casaux-Bic

Yvan Ludovic Lameignere

Christophe Ludovic Jean-Claude Viguier

Albert Josse

Disclosed is a turbogenerator, in particular for an electrically-driven rotary wing aircraft, comprising a gas generator equipped with a first shaft, at least one reversible electrical machine, and a free turbine provided with a second shaft and caused to rotate by a gas flow generated by the gas generator. The second shaft is coupled to the at least one electrical machine during all phases of operation of the turbomachine, and the turbomachine further comprises a single mechanical coupling means for coupling the first mechanical shaft to the second mechanical shaft when the electrical machine is operating in motor mode and mechanically uncoupling the first mechanical shaft from the second mechanical shaft when the electrical machine is operating in generator mode.

Free turbine turbogenerator comprising a reversible electrical machine coupled to the free turbine

A hybrid propulsion system for a multi-rotor rotary-wing aircraft, including: an internal combustion engine, an electric machine coupled to the internal combustion engine, a rectifier connected to the electric machine, a converter, an electric network connecting the rectifier to the converter, electric motors connected to the converter, rotary-blade assemblies coupled to the electric motors, wherein the system includes: a detector configured to detect a reduction in a demand for electrical power within the system to below a predetermined value, a bypass circuit configured to bypass the electric machine when the detector detects a reduction in the demand for electrical power.

Hybrid propulsion system and method for controlling such a system

Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.

Recovered-cycle aircraft turbomachine

Disclosed is a turbomachine, comprising a gas generator () equipped with a first shaft (), at least one reversible electrical machine (), a free turbine () provided with a second shaft () and caused to rotate by a gas flow generated by the gas generator (), an accessory gear box () and at least one accessory (). Said at least one electrical machine () is mechanically coupled to said second mechanical shaft () via the accessory gear box () during all phases of operation of the turbomachine (), the accessory gear box () is coupled to the at least one accessory () and the turbomachine () further comprises a single mechanical coupling means () for mechanically coupling said first mechanical shaft () to the accessory gear box () in a first configuration and mechanically uncoupling said first mechanical shaft () from the accessory gear box () in a second configuration.

Free turbine turbomachine comprising equipment driven by the free turbine

A turbomachine including a gas generator endowed with a first shaft, a gear box, at least one reversible electric machine coupled to the gear box, and a free turbine endowed with a second shaft and rotationally driven by a gas stream of the gas generator and at least one accessory coupled to the accessory gear box, wherein the turbomachine includes a first mechanical coupling means configured to mechanically couple said first mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said first mechanical shaft from the accessory gear box in a second configuration, and a second mechanical coupling means configured to mechanically couple said second mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said second mechanical shaft from the accessory gear box in a second configuration.

Free-turbine turbomachine comprising equipment driven by the free turbine

A hybrid propulsion chain for an aircraft, the hybrid propulsion chain comprising a plurality of propulsion rotors connected to an electrical distribution module by a plurality of electrical connections, the electrical distribution module being connected, on the one hand, to a non-propulsion turbine engine via an electrical generation system and, on the other hand, to an electric battery, each propulsion rotor comprising a stator member and at least one rotor shaft which is configured to be rotated with respect to the stator member when the stator member is electrically powered, the hybrid propulsion chain comprising an auxiliary mechanical drive system mechanically connected to the non-propulsion turbine engine, the auxiliary mechanical drive system comprising a plurality of mechanical connections for mechanically rotating at least one rotor shaft of each propulsion rotor.

Hybrid propulsion chain for an aircraft comprising an auxiliary mechanical drive system

An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.

A component () for supporting at least one bearing () for a turbine engine () comprising: two coaxial walls, internal () and external () walls respectively, defining a gas flow vein () between them and interconnected by a row of arms (); an external ferrule () comprising an internal peripheral edge () connected to the external wall () and an external peripheral edge () connected to an external mounting flange (); an internal ferrule () comprising an external peripheral edge () connected to the internal wall () and an internal peripheral edge () comprising an internal mounting flange (); at least one of the ferrules (), which at the peripheral edge () thereof is connected to the corresponding wall (), having a general shape which is corrugated about an axis (X-X) of the component ().

Annular component for supporting a turbine engine bearing

The present invention relates to an electric machine for an aircraft, comprising a stator and a rotor that is rotationally mobile with respect to the stator, the rotor or the stator comprising a plurality of permanent magnets, the machine comprising a device for demagnetising a permanent magnet, suitable for achieving a temporary increase in the temperature of the permanent magnet, in order to limit, during the temporary increase in temperature, an exciting magnetic flux generated by the permanent magnet. The present invention furthermore relates to an assembly comprising an assembly comprising such an electric machine and a hot-fluid source suitable for delivering hot fluid to the demagnetising device of the electric machine. The hot-fluid source may be a gas stream of a turbine engine.

Electric machine with device for forcibly demagnetising permanent magnets

A turbomachine, particularly for a rotary-wing aircraft, including a gas generator provided with a rotary shaft, a first reversible electric machine, a power turbine rotationally driven by a stream of gas generated by the gas generator, at least one accessory from among an oil pump and a fuel pump, an accessory gearbox comprising a gear train configured to drive said at least one accessory, and a second electric machine. The second electric machine is reversible, said first electric machine is mechanically coupled to the gas generator, the accessory gearbox and the second electric machine are mechanically coupled to the power turbine, and the turbomachine is devoid of any kinematic coupling between the gear train of the accessory gearbox and the shaft of the gas generator.

Turbomachine having a free turbine comprising electric machines assisting a gas generator and a free turbine

An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.

Growing community of inventors

Moissy-Cramayel, France

Loïs Pierre Denis Vive