Safran Helicopter Engines

Safran

Safran Power Units

Safran Aircraft Engines

Safran Electronics & Defense

Safran Electrical & Power

Turbomeca

Camel Serghine

Thomas Klonowski

Romain Thiriet

Loïs Pierre Denis Vive

Vincent Poumarede

Laurent Pierre Tarnowski

Patrick Marconi

Jean-Louis Robert Guy Besse

Sabrina Siham Ayat

Pierre Yvart

Fabien Mercier-Calvairac

Stéphane Beddok

Stephen Langford

Olivier Lafargue

Jean-Michel Bazet

Laurent Fabbri

Thomas Drouin

Bertrand Moine

Jean-Luc Charles Gilbert Frealle

Caroline Seve

Denis Antoine Julien Real

Thomas Barraco

Alphonse Puerto

Jean-Julien Camille Vonfelt

Laurent Soulie

Pierre Darfeuil

Frederic Moulon

Didier Claude Chartrain

François Danguy

Antoine Marie Georges Caratge

Philippe Barrat

Stéphane Richard

Thomas Michel Andre Gerard Barraco

Olivier Robert

Caroline Maud Léna Seve

Albert Mutabazi

Sébastien Yon

Eric Rouland

Pierre Gabriel Marie Quinio

Jérôme Irigoyen

Pierre-Luc Regaud

Christian Sarrat

François Porel

Guillaume Demezon

Sebastien Combebias

Sébastien Combebias

Jean-Michel Sannino

Pascal Guillemet

Nicolas Marucheau De Chanaud

Frédéric Moulon

Seve Caroline Maud Léna

Francois Danguy

Stephane Richard

Stephane Beddok

Jean-Louis Besse

Jerome Irigoyen

Antoine Marie Caratge

Francois Porel

Michael Derderian

Vincent Duqueine

A propulsion unit with a propeller is provided, having a nacelle and a propeller rotatably mounted in the nacelle by a hub. The propeller includes blades mounted in a blade cuff pivotable about a pitch axis relative to the hub, each blade being pivotable relative to the cuff about a folding axis. The propulsion unit can further include a folding device that comprises an actuator for folding the blades. The folding device can include a control member rotationally affixed to the blade cuff and driven by the actuator, and a connecting rod pivotably mounted, on the one hand, on a root of the associated blade and, on the other hand, on the movable control member.

Propulsion unit with foldable propeller blades and method for folding the blades

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 propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position (θ i) relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

Propulsion unit with foldable propeller blades and method for stopping the propeller in an indexed angular position

A propulsion unit with a propeller includes a nacelle; a propeller rotatably mounted in the nacelle by means of a hub. The propeller has blades mounted in a blade cuff that is pivotable about a pitch axis relative to the hub. Each blade is pivotable relative to the cuff about a folding axis. A folding device includes an actuator for folding the blades. The folding device includes a control member rotationally affixed to the blade cuff and driven by the actuator. A connecting rod is pivotably mounted, on the one hand, on a root the associated blade and, on the other hand, on the movable control member.

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

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 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

A turbogenerator () for an aircraft () comprising: a turboshaft engine (); an electric generator () comprising a rotor () driven mechanically by the turboshaft engine () and a stator () supported by a housing () of the electric generator (); characterized in that the turbogenerator () comprises a static separator () for separating an air/oil mixture coming from the turboshaft engine (), the static separator () being positioned around the housing () of the electric generator ().

Turbogenerator for aircraft, comprising an improved oil system

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

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (), characterised in that it comprises a pneumatic turbine () mechanically connected to said turbine engine () so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage () connected to said pneumatic turbine () by means of a pneumatic circuit () for supplying pressurised gas to said pneumatic turbine (); a controlled fast-opening pneumatic valve () arranged on the pneumatic circuit () between said storage () and said pneumatic turbine () and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (), or in a closed position in which said pneumatic turbine () is no longer supplied with pressurised gas.

Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter

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

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Boeil-bezing, France

Camel Serghine