Safran Helicopter Engines

Safran Power Units

Peugeot Citroen Automobiles Sa

Fabien Mercier-Calvairac

Romain Thiriet

Stéphane Beddok

Sophie Humbert

Camel Serghine

Thomas Klonowski

Vincent Poumarede

Romain Jean Gilbert Thiriet

Nawal Jaljal

Frederic Moulon

Antoine Drachsler

Vincent Mulot

Stéphane Chevalier

Eric Pierre Seinturier

David Le Maux

Stéphane Albert André Douillard

Stephane Chevalier

Stephane Beddok

Frédéric Moulon

Patrick Lagonotte

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

The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.

Helicopter equipped with a device for emergency lift assistance

An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.

Architecture of a multiple-engine helicopter propulsion system, and corresponding helicopter

The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. Each of the electric powertrains is adapted to deliver maximum power not less than half the total power needed for rapid reactivation of the hybrid engine.

Hybrid propulsion system for a multi-engine aircraft

The invention relates to a method and to a device for optimized global management of a power network of an aircraft comprising a plurality of items of power equipment, characterized in that it comprises a modulefor selecting at least one optimization objective () from a plurality of predetermined objectives, a module () for receiving equipment data, a module () for receiving aircraft data, and a module () for determining operating setpoints () of the power equipment from equipment data () and aircraft data () which is suitable for achieving at least one selected optimization objective ().

Method of optimized global management of an energy network of an aircraft and corresponding device

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines () that are connected to a power transmission gearbox (), and comprising a low DC voltage onboard network () for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine () that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack () for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack () being connected to said onboard network (); and at least two sources () of electrical power for said onboard network ().

Architecture of a multi-engine helicopter propulsion system and corresponding helicopter

An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.

Assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines

Growing community of inventors

Pau, France

Fabien Mercier-Calvairac