Safran Helicopter Engines

Safran

Safran Electrical & Power

Safran Electronics & Defense

Other

Turbomeca

Safran Power Units

Alstom Transport Sa

Labinal Power Systems

Klonowski, Thomas

Thomas Klonowski

Camel Serghine

Loïs Pierre Denis Vive

Antoine Pascal Moutaux

Vincent Poumarede

Olivier Lafargue

Thomas Barraco

Jean-Julien Camille Vonfelt

Sabrina Siham Ayat

Michel Nollet

Fabien Mercier-Calvairac

Stéphane Beddok

Jean-Michel Bazet

Bertrand Nogarede

Jean-Luc Charles Gilbert Frealle

Pierre Harriet

Ludovic Meziere

David Cazaux

Caroline Maud Léna Seve

Albert Mutabazi

Olivier Robert

Sébastien Yon

Eric Rouland

Thomas Michel Andre Gerard Barraco

Frédéric Pailhoux

Pierre Gabriel Marie Quinio

Bernard Plissonneau

Olivier Audrey David Lafargue

Christophe Aubigny

Frederic Pailhoux

Ludovic Ybanez

Stéphane Richard

Sebastien Combebias

Stephane Beddok

Stephane Richard

Seve Caroline Maud Léna

Thomas Baracco

A method for protecting coils from excessive heating in an aircraft electrical machine comprising a stator and a rotor configured to be rotationally driven with respect to one another, the stator including a plurality of notches receiving one and the same plurality or otherwise of coils, the method including the following successive steps:

Aircraft electrical machine with improved heat transfer by means of a phase change material and associated method

A method for starting an aircraft engine in which the engine is coupled to a lubrication circuit including an oil pump system, the lubrication circuit being constructed and arranged to circulate oil in the engine, and in which an operating mode of the engine includes a stop mode and a standby mode, the starting method including, during a starting phase, measuring an oil temperature, the measurement being performed by a temperature detection device; depending on the temperature measured, compared to a threshold temperature, and depending on the operating mode of the engine, select a starting oil flow profile to be applied in said engine, the selection being performed by a calculator, and applying the selected starting oil flow profile by the oil pump system, the oil pump system being controlled by the calculator.

Method for starting an aircraft engine

A hybrid/electric propulsion architecture for a multi-rotor rotary wing aircraft, including an electricity generator driven by an internal combustion engine, and configured to operate in motor mode, a rectifier configured to convert an alternating current delivered by the electricity generator into direct current, an electrical network including a high voltage direct current (HVDC) bus, electrical energy storage means connected to the electrical network, during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means: the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.

Hybrid-electric propulsion architecture and method for dissipating electrical energy in such an architecture

A hybrid propulsion system for a multi-rotor rotary-wing aircraft, including: an internal combustion engine, an electric machine coupled to the internal combustion engine, a rectifier connected to the electric machine, a converter, an electric network connecting the rectifier to the converter, electric motors connected to the converter, rotary-blade assemblies coupled to the electric motors, wherein the system includes: a detector configured to detect a reduction in a demand for electrical power within the system to below a predetermined value, a bypass circuit configured to bypass the electric machine when the detector detects a reduction in the demand for electrical power.

Hybrid propulsion system and method for controlling such a system

A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the rectifier to the converter and including a high-voltage DC current bus, electric motors powered by propeller converters coupled to the electric motors, electrical energy storage connected to the electrical network, the electrical storage including at least one primary storage element and at least one secondary storage element.

Hybrid propulsion unit for an aircraft

A hybrid propulsion chain for an aircraft, the hybrid propulsion chain comprising a plurality of propulsion rotors connected to an electrical distribution module by a plurality of electrical connections, the electrical distribution module being connected, on the one hand, to a non-propulsion turbine engine via an electrical generation system and, on the other hand, to an electric battery, each propulsion rotor comprising a stator member and at least one rotor shaft which is configured to be rotated with respect to the stator member when the stator member is electrically powered, the hybrid propulsion chain comprising an auxiliary mechanical drive system mechanically connected to the non-propulsion turbine engine, the auxiliary mechanical drive system comprising a plurality of mechanical connections for mechanically rotating at least one rotor shaft of each propulsion rotor.

Hybrid propulsion chain for an aircraft comprising an auxiliary mechanical drive system

Methods for controlling an electrical power supply network for an aircraft, include pre-charging at least one capacitor in a normal operating mode when a gas turbine is available, pre-charging the at least one capacitor in a backup operating mode when the gas turbine is not available, and discharging the at least one capacitor at the end of use of the electrical power supply network when the at least one capacitor is charged.

Method for controlling an electrical power supply network for an aircraft

An assembly including a winding and a cooler in contact with conductors of the winding, the cooler including a container forming a heat dissipator and including a phase change material having the ability to absorb a surplus quantity of heat when the conductors of the winding are subject to an increase in their current density and the heat dissipator is composed of at least two hollow parts separate and nestable with one another and intended to house the phase change material.

Electrical machine winding having improved cooling

The invention relates to an aircraft power architecture comprising a power transmission gearbox (), located in a first compartment (), a gas turbine (), located in a second compartment () comprising a gas generator () and a free turbine () connected to the power transmission gearbox () by a power shaft () of the gas turbine (), and an accessory gearbox (), the gas turbine () being set into the main transmission gearbox (), characterized in that the gas turbine () comprises a first electric machine (), and in that the accessory gearbox () is placed in the first compartment () and comprises a second electric machine () configured to supply energy to the accessory equipment and to receive electrical energy transmitted via the first electric machine ().

Aircraft power architecture

The present invention relates to an electric machine for an aircraft, comprising a stator and a rotor that is rotationally mobile with respect to the stator, the rotor or the stator comprising a plurality of permanent magnets, the machine comprising a device for demagnetising a permanent magnet, suitable for achieving a temporary increase in the temperature of the permanent magnet, in order to limit, during the temporary increase in temperature, an exciting magnetic flux generated by the permanent magnet. The present invention furthermore relates to an assembly comprising an assembly comprising such an electric machine and a hot-fluid source suitable for delivering hot fluid to the demagnetising device of the electric machine. The hot-fluid source may be a gas stream of a turbine engine.

Electric machine with device for forcibly demagnetising permanent magnets

In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.

Multi-rotor aircraft propulsion system with reconfigurable electric network

In order to reduce the weight of a hybrid propulsion system for a multi-rotor rotary-wing aircraft, the system comprises at least one inverter configured to supply power in parallel to multiple electric motors intended to drive the corresponding propellers of the system.

Hybrid propulsion system for multi-rotor rotary wing aircraft, comprising improved DC/AC conversion means

The invention relates to an aircraft propulsion system, comprising a main transmission unit () and at least two turbojet engines connected to the main transmission unit (), respectively a first turbojet engine () and a second turbojet engine (), each turbojet engine comprising a free turbine (), characterized in that the first turbojet engine () comprises a heat exchanger () configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer () configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine () when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger ().

Asymmetric propulsion system with heat recovery

The invention relates to an electrical machine comprising a stator () and a rotor () designed to be rotated in relation to each other, said rotor () or said stator comprising a plurality of permanent magnets (), at least one permanent magnet comprising at least one fluid-propagation channel () extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.

Electrical machine of a turbomachine comprising a rotor cooled by a cooling channel

An electric machine includes a stator and a rotor configured to be driven in rotation in relation to one another. The rotor includes a plurality of permanent magnets, and the stator further includes a magnetic circuit including poles extending toward the rotor. The machine includes windings of conducting elements around each pole and at least one heat sink arranged inside a conducting element and/or between the conducting elements. The heat sink includes a phase change material.

Electric machine with phase change material for a turbomachine starter/generator

Growing community of inventors

Moissy-Cramayel, France

Thomas Klonowski