Safran Helicopter Engines

Safran Electrical & Power

Safran Power Units

Romain Jean Gilbert Thiriet

Antoine Pascal Moutaux

Benjamin Fulleringer

Olivier Bedrine

Fabien Mercier-Calvairac

David Bernard Martin Lemay

Denis Antoine Julien Real

Stéphane Meyer Beddok

Fabien Mercier-calvairac

Valéry Chau

Stéphane Albert André Douillard

Eric Jean-Louis Bouty

Antoire Pascal Moutaux

Stephane Albert Andre Douillard

A propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

Propulsive assembly for a multi-engine hybrid aircraft

A device for controlling a power-transfer system for the transfer of power between a high-pressure shaft and a low-pressure shaft of a turbomachine of an aircraft, including a fatigue analysis module analysing the fatigue of the turboma-chine and designed to determine, from between two indicators (D, D) respectively measuring two fatigues of the turbomachine, which is the one that is the most advanced, which is to say which is the one at risk of being first to reach a respective upper limit (Dmax, Dmax); and—a control module controlling the power transfer system and designed to slow the fatigue measured by the more advanced indicator (D, D).

Transfer of power between the high-pressure shaft and the low-pressure shaft of a turbomachine

Hybrid turbomachine comprising an electric generator, a gas generator-equipped with an air inlet and with an exhaust and an acoustic monitoring system comprising a control unit and a plurality of loudspeakers. At least a first loudspeaker is disposed on the electric generator, and/or at least a second loudspeaker is disposed on the air inlet of the gas generator, and/or at least a third loudspeaker is disposed on the exhaust of the gas generator. The control unit of the acoustic monitoring system is mounted on the electric generator and is configured to make an AC-DC electrical conversion of the electromotive force of the electric generator into an adjustable DC voltage intended to be distributed to loads or to energy storage means.

Hybrid turbomachine for aircraft with an active acoustic control system

Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.

Hybrid propulsion system for a helicopter

A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

Transmission device for hybrid aircraft

A propulsion system () for a helicopter, comprising a turboshaft engine () with a linked turbine and an electric machine () capable of operating as an electric motor, the turboshaft engine () and the electric machine () being capable of driving in rotation at least one main rotor () intended to be coupled to a rotating wing () characterised in that it comprises means of coupling and decoupling () in rotation between a rotor () of the electric machine () and a rotor () of the turboshaft engine (), the means of coupling and decoupling () being capable of allowing the rotor () of the turboshaft engine () to be driven in rotation with the aid of the electric machine (), in a first state of the propulsion system (), and capable of allowing the rotor () of the turboshaft engine () and the rotor () of the electric machine () to be decoupled in rotation, in a second state of the propulsion system ().

Propulsion system for a helicopter

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 branch, a plurality of electric motors actuating a same plurality of rotors providing together the propulsion and/or the lift of the aircraft, and an electrical power and distribution unit supplying power to the plurality of electric motors from the electricity generator and/or from the electrical energy storage assembly according to a pre-established flight phase, the system including at least two energy branches having an asymmetric configuration and each supplying power selectively, by means of the electrical power and distribution unit, all or part of the plurality of electric motors, and in that the electricity generators of the combustion engines have between them a power ratio comprised between.

Growing community of inventors

Moissy-Cramayel, France

Romain Jean Gilbert Thiriet