Safran

Safran Electrical & Power

Christelle Saber

Cyrille Gautier

Anthony Gimeno

Sébastien Merle

Florent Rougier

Toni Youssef

Sabrina Siham Ayat

Marwan Ali

Mallika Nadheria

Adrian Florescu

An aircraft thruster includes at least a first propeller provided with a plurality of radial blades extending about an axis of rotation of the said first propeller, which is driven in rotation by a first electric motor. An electrical supply of the first electric motor includes power circuits carried by a fairing of the thruster characterized in that the power circuits are arranged in an annular manner in an annular part integral with the fairing of the thruster, this annular part being arranged around the said first propeller.

Aircraft thruster having an annular part integral with a fairing surrounding a first propeller

A method for determining a first setpoint for a first vector component of the phase currents along a first axis of a rotating reference frame connected to a rotor of the electric generator, and a second setpoint for a second vector component of the phase currents along a second axis of the rotating reference frame. The second vector component of the phase currents is to bring about defluxing of the rotor; and controlling the rectifier on the basis of the first and second setpoints for the vector components of the phase currents. The first setpoint for the first vector component of the phase currents is determined on the basis of an external feedback loop designed to feedback-control a voltage on a DC bus or to regulate a current from a battery connected to the DC bus.

Method for controlling a rectifier connected to a permanent-magnet synchronous electric generator to provide a direct voltage, corresponding device and computer program

A system configured to deliver as output a polyphase current of constant frequency from a synchronous generator driven at variable speed. The system includes, at the output of the generator, an AC-to-DC active rectifier including one arm per phase of the current, a DC bus and a DC-to-AC inverter for the output including one arm per phase of the current, the inverter or the DC bus including an arm connected to the neutral, each arm including a controllable switch, the system including an electronic control unit driving the rectifier and including means for tracking a voltage for the rectifier and/or the inverter and means for controlling the inverter, the system including an EMC filter including one arm for each phase of the current, each arm including an inductor, a capacitor connected in a bypass downstream of the inductor, the arm connected to the neutral being connected to each bypass.

System configured to deliver a polyphase current of constant frequency from a synchronous generator

Polyphase electrical machine with n phases, n&#x2265;3, including a casing defining a longitudinal axis, a stator and a rotor including a mechanical drive shaft, the electrical machine being equipped with a power electronics and a coolant circuit and the power electronics is formed of n power electronic modules evenly distributed over an inner circumference of a longitudinal extension of the casing whose outer circumference is covered with a single annular DC bus decoupling capacitor electrically connected to the n power electronic modules, the coolant circuit including a plurality of U-shaped tubes with a tubular outgoing part extending over an entire length of the casing and including the longitudinal casing extension and a shorter tubular return part, extending over a casing length excluding the longitudinal casing extension.

Polyphased electrical machine with integrated power electronics and an integrated coolant circuit

The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

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Moissy-Cramayel, France

Christelle Saber