Safran Helicopter Engines

Safran

Safran Electrical & Power

Safran Power Units

Peugeot Citroen Automobiles Societe Anonyme

Stéphane Beddok

Fabien Mercier-Calvairac

Sophie Humbert

Camel Serghine

Thomas Klonowski

Florent Rougier

Vincent Poumarede

Jean-Michel Bazet

Garance Vinson

Stéphane Chevalier

Stéphane Richard

A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement.

Method and system for regulating a non-propulsion electrical generation turbomachine

Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (V), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.

Method and device for monitoring the hybridization of an aircraft

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 invention relates to the field of magnetohydrodynamic generators, and more precisely to such a generator () comprising a working fluid flow passage () that is defined by a first wall () and a second wall (), an ionizing device () for ionizing the working fluid, a pair of arms (), each connecting together the first and second walls () downstream from said ionizing device () so as to define, within the flow passage (), a channel () between said arms () and said walls (), said channel () being arranged to be traversed by a portion of the working fluid after it has been ionized, a magnet for generating a magnetic field (B) oriented in a direction that is perpendicular to the flow of the working fluid through the channel () defined by the pair of arms () and said walls (), and at least one pair of electrodes (), each of the electrodes () in each pair being arranged on a respective side of the channel () defined by the pair of arms () and said walls (), said electrodes () in each pair being spaced apart from each in a direction that is perpendicular to said magnetic field (B) and to the flow direction of the working fluid through the channel () defined by the pair of arms () and by said walls ().

Magnetohydrodynamic generator

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

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 ().

Growing community of inventors

Pau, France

Stéphane Beddok