Safran Aircraft Engines

Nicolas Bertrand Georges De Blois

Clément Dupays

Huguette De Wergifosse

Pierre Gerard Lalonde

An actuation system includes: a generating rotating electrical machine including a first stator including at least one output stator winding; a driving rotating electrical machine including a second rotor, intended to actuate a lubrication pump, and a second stator including at least one input stator winding; an array of switches electrically connected to the at least one output stator winding and to the at least one input stator winding, for electrically connecting them together or disconnecting them from each other depending on the state of the array of switches; and a control device configured to control the array of switches, depending on the state of a control signal, in such a way as to electrically connect or not connect the at least one output stator winding and the at least one input stator winding together.

Actuation system for an aircraft engine lubrication pump and associated aircraft

In an electromechanical actuation chain for controlling the movement of mobile loads of an aircraft turbine engine, from a control unit, one or more of these mobile loads being actuated by an electromechanical actuator, there is provided for control of this movement a single Ethernet controller having deterministic control that uses an Ethernet bus to control a set of converters acting selectively on the electromechanical actuators.

Pooled architecture for controlling electromechanical actuators

The invention concerns a bypass turbomachine () with a primary flow path and a secondary flow path, comprising: —a low-pressure body comprising a low-pressure compressor () connected to a low-pressure turbine () via a low-pressure shaft (), —a high-pressure body comprising a high-pressure compressor () connected to a high pressure turbine (), via a high-pressure shaft (), —a low-pressure power take-off system () comprising an electrical generator (), configured to take power (W) from the low-pressure body, wherein—the turbomachine comprises a debris removal system (), located between the two compressors (), —the low-pressure power take-off system () is configured to take power (W) from the low-pressure shaft () using the resistive torque of the electrical generator (), in order to avoid a risk of surging.

Power withdrawal from a LP body and system for removing debris

A power distribution device between an electric starter of a turbomachine and an electric machine toward a shaft of the turbomachine, including the electric starter, the electric machine, and a controller for controlling the electric machine. An epicyclic train reducer includes a first element intended to be coupled to the shaft, a second element coupled to the electric starter, and a third element intended to be rotated by the electric machine. The controller is configured to rotate the third of the three elements so as to obtain two bearings of reduction ratios of the speeds between the first of said three elements and the second of the three elements. The controller is configured to drive the torque of the third of the three elements in accordance with a determined output torque.

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Moissy-Cramayel, France

Nicolas Bertrand Georges De Blois