Safran

Commissariat &#xc0; L'&#xc9;nergie Atomique Et Aux &#xc9;nergies Alternatives

Peugeot Citroen Automobiles Sa

Nawal Jaljal

Samer Maalouf

Fabien Mercier-Calvairac

Pierre Dumoulin

Nicolas Tauveron

Panagiotis Giannakakis

Vincent Mulot

Fabien Desarnaud

Patrick Lagonotte

An electrical assembly for an aeronautical turbomachine, including an electric machine configured to be disposed in a turbomachine and comprising a stator and a rotor comprising magnets, the assembly including a short-circuit detecting means, a hot air injecting means configured to draw hot air off the turbomachine at a temperature greater than the temperature of demagnetization of the magnets of the rotor, and to inject the drawn hot air onto the magnets of said rotor when the short-circuit detecting means detects the presence of a short-circuit in the electric machine, and a cool air injecting means, configured to draw cool air off the turbomachine and to inject it into an inner chamber of the turbomachine, the temperature of the cool air drawn by the cool air injecting means being less than the temperature of the hot air drawn by the hot air injecting means.

Device and method for stopping an electric machine for a turbine engine

The invention relates to a method for controlling a turbomachine comprising a gas generator, the turbomachine comprising an electric machine forming a device for injecting torque into/removing torque from one of the low pressure/high pressure rotation shafts of said gas generator. Said method comprises a step of implementing a fuel control loop in order to determine a fuel flow setpoint into the combustion chamber, and comprising, in the event that at least one operability limit is reached, determining a corrected fuel flow setpoint, said corrected fuel flow setpoint exhibiting a difference in relation to the setpoint. Said method also comprises a step of implementing a torque control loop in order to determine a torque setpoint for the electric machine, and comprising determining a torque correction quantity as a function of said difference, said torque setpoint being determined as a function of said torque correction quantity.

Method for controlling a turbomachine comprising an electric machine

The aircraft motor architecture comprises two reversible electric machines (), the rotors () of which are linked both to the low pressure shaft () and to the high pressure shaft () by transmissions () alternately disengaged depending on the direction of rotation of the rotor (), the transmissions comprising passive one-way clutches (), the engagement directions of which are opposed. Independent modes of operation of the machines, as a starter or as an electric generator of each of the shafts, are thus provided.

Hybrid propulsive architecture for an aircraft comprising an engine with a reversible electric machine mounted on two shafts

A cooling system for cooling a circuit of a first fluid of a turbomachine, the cooling system including a refrigerant fluid circuit including a first heat exchanger for exchanging heat between the refrigerant fluid and air, a second heat exchanger for exchanging heat between the refrigerant fluid and the first fluid, an expander located downstream from the first heat exchanger and upstream from the second heat exchanger in the flow direction of the refrigerant fluid, and a compressor located downstream from the second heat exchanger and upstream from the first heat exchanger; the cooling system further includes a third heat exchanger of the first fluid and air type.

System for cooling a circuit of a first fluid of a turbomachine

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Moissy-Cramayel, France

Nawal Jaljal