Safran Helicopter Engines

Safran Electrical & Power

David Bernard Martin Lemay

Antoine Pascal Moutaux

Romain Jean Gilbert Thiriet

Jean-Luc Charles Gilbert Frealle

Stéphane Meyer Beddok

Pierre Anthony Sicaire

Julien Marc Nicolas Rambaud

Fabien Mercier-calvairac

Alexis Thomas Valentin Longin

Jean-Philippe Jacques Marin

Philippe Jean Rene Marie Benezech

A method for regulating the speed of a propulsion device of an aircraft including: the propulsion device and a gearbox MGB; the heat engine and at least one electric motor, mounted in parallel on the MGB, the heat engine having a fuel circuit; main and backup regulation systems, and a regulation system, each capable of regulating the speed of the heat engine or the electric motor, respectively; a control system of the aircraft, capable of sending a speed or power setpoint to each of the regulation of the heat engine and the electric motor. The method includes: sending a speed setpoint Nto the regulation system of the electric motor, the regulation system sending a power command P, to obtain an instantaneous power P; simultaneously, sending a speed or power command to the backup regulation system of the heat engine, the backup regulation system sending a selected fuel flow command QCarbAux* to the fuel circuit of the heat engine.

Method for regulating the speed of rotation of a propulsion device of a hybrid propulsion unit for an aircraft, in the event of a failure of the main regulation system of the heat engine of the hybrid propulsion unit

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

The present invention relates to a device () for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller () and at least one electric motor () that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (). The control device () comprises at least a unit () for measuring an electric supply voltage, and a control unit () suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

Device for controlling a least one electric motor for an aircraft-propelling assembly

A system for pumping and metering a fluid for a turbine engine, which system includes at least one pump for the fluid and an electronic computer configured to determine the flow rate of the fluid to be delivered to the turbine engine, the pumping and metering system being wherein it further includes a first electric motor and a second electric motor, which are each configured to drive the at least one pump, and in that the electronic computer includes a first control loop for controlling at least the first electric motor and a second control loop for controlling at least the second electric motor.

System for pumping and metering a fluid for a turbine engine and method for controlling such a system

Growing community of inventors

Moissy-Cramayel, France

David Bernard Martin Lemay