Safran Helicopter Engines

Safran Electrical & Power

Valeo Equipments Electriques Moteur

Valeo Equipements Electriques Moteur

Jean-Michel Bazet

Philippe Vallart

Camel Serghine

Thomas Klonowski

Romain Thiriet

Patrick Marconi

Vincent Poumarede

Stephen Langford

Ertugrul Taspinar

Stéphane Beddok

David Huart

Marcel Vogelsberger

Pierre Harriet

C&eacute;dric Plasse

Cédric Plasse

Loïc Le Duigou

Jérôme Irigoyen

Loic LeDuigou

Jerome Irigoyen

Loic Le Duigou

The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.

Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine

The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine () capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems () for controlling each hybrid turboshaft engine (), each system () comprising an electric machine () connected to the hybrid turboshaft engine () and suitable for rotating the gas generator thereof, and at least one source () of electrical power for said electric machine (), each reactivation system () being configured such that it can drive said turboshaft engine () in at least one operating mode among a plurality of predetermined modes.

An assistance device for an aircraft free-turbine turbine engine, the device including first electrical power supply for powering a winding of a starter rotary machine, referred to as a 'first' winding, in order to provide first assistance in accelerating the gas generator of the engine. The device further includes a monitor for monitoring the first assistance, and a second power supply for electrically powering a second winding of the rotary machine to provide second assistance in accelerating the gas generator if the monitor observes that the first assistance is insufficient.

Assistance device for an aircraft turbine engine with a free turbine

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Device and method for testing the integrity of a helicopter turbine engine rapid restart system

A transmission assembly for an aircraft, and a helicopter including such an assembly for controlling independently the speed of rotation of an engine and of a torque receiver. According to the invention, the assembly comprises a first inlet shaft () configured to receive torque from a first engine (), an outlet shaft () configured to transmit torque to a torque receiver (), a first transmission member () having at least two degrees of freedom and comprising first, second, and third movable portions, a first reversible electrical regulator machine (), and a first reversible electrical balancing machine (), wherein the inlet shaft () is coupled to the first movable portion, the outlet shaft () is coupled to the second movable portion, the first electrical regulator machine () is coupled to the third movable portion, and the first electrical balancing machine () is coupled in series with the inlet shaft or the outlet shaft ().

Transmission assembly for an aircraft and a helicopter

Electric supply device, in particular for motor vehicle on-board network

Growing community of inventors

Gelos, France

Jean-Michel Bazet