Safran Aircraft Engines

Emmanuel Fabrice Marie Baret

Julien Fabien Patrick Becoulet

Paul Ghislain Albert Levisse

Michel Gilbert Roland Brault

Alexandre Jean-Marie Tan-Kim

Franck Emmanuel Bosco

Tewfik Boudebiza

Pierre-Alain Jean Philippe Reigner

Jean-Claude Christian Taillant

A turbomachine for an aircraft comprising a stator, a turbine shaft and an electric machine arranged to the rear of the turbine shaft, and comprising an electric machine stator and an electric machine rotor, a rotationally fixed coupling carriage capable of moving in axial translation relative to the electric machine rotor between coupled and uncoupled positions, coupling members which are designed to engage with one another after the coupling carriage has moved from the uncoupled position to the coupled position and to transmit a torque from the turbine shaft to the electric machine rotor when they are engaged, and an elastic return member designed to elastically return the coupling carriage in axial translation to the coupled position.

Aircraft turbomachine comprising an electric machine

A device for centering and guiding a shaft of an aircraft turbine engine is provided. The device includes an outer ring of a rolling bearing extending about an axis and having orifices, an annular bearing support extending about the axis and at least partially about the ring, the support having orifices and a series of studs for connecting the ring to the support. The studs can be distributed about the axis and extend parallel to the axis. The ends of first studs can be engaged without clearance in the orifices, and ends of second studs can be engaged with clearances in the orifices of the ring and/or of the support, the clearances being configured so that the device has different stiffnesses in at least two directions perpendicular to the axis.

Device for centering and guiding a shaft of an aircraft turbine engine

The invention relates to a planetary gear reducer () for an aircraft turbine engine (), the reducer () comprising a sun gear () and a ring gear () which are centred on a longitudinal axis X and a planet carrier () which carries at least one planet gear () rotatably mounted about a planet axis A parallel to the longitudinal axis X, the sun gear () being rotatable about the longitudinal axis, the planet gear () meshing both with the sun gear () and the ring gear (), the planet carrier () being movable about the longitudinal axis and the ring gear () being rotationally fixed. According to the invention, the reducer () comprises an electric machine () integrated therewith and which comprises a rotor () mounted on the planet carrier () in such a way as to be rotated about the longitudinal axis X and a stator () mounted on the ring gear ().

Speed reducer equipped with an electric machine

A device for centering and guiding a shaft of an aircraft turbine engine, the device including an outer ring of a rolling bearing, the ring extending about an axis; an annular bearing support extending about the axis and at least partially about the ring; at least one series of connecting elements for linking the ring to the support, the connecting elements being interposed between an inner cylindrical rim of the ring and an outer cylindrical rim of the support that extends about the inner rim, and each having a first radially outer end for linking to the outer cylindrical rim and a second radially inner end for linking to the inner cylindrical rim, the ring, the support and the connecting elements being integrally formed, the connecting elements being enclosed in an annular housing that is radially delimited by the rims and laterally enclosed by an annular web.

A device for centering and guiding a shaft of an aircraft turbine engines. The device includes an outer ring of a rolling bearing, the ring extending about a main axis and having orifices arranged around the axis axis; an annular bearing support extending about the main axis and at least partially about the ring, the support having orifices and openings arranged about the axis; and a series of studs for linking the ring to the support, the studs being distributed about the main axis and having elongation axes substantially parallel to the main axis, the body of each of the studs passing through one of the openings. Some of the studs, have bodies that pass with a first positive clearance and a second virtually zero clearance through the first openings, the first and second clearances being configured so that the device has different displacement amplitudes.

A pump that can be a gear pump that drives a rotating body of an aircraft turbine engine such as a fan shaft, is set in rotation always in the same direction, by virtue of a transmission including an oblique double gear formed by a toothed wheel on the same side as the rotating body and meshing with two pinions connected to a shaft driving the pump through free-wheels with identical driving directions, whereas the pinions have opposite directions of rotation.

Aircraft turbomachine arrangement comprising a lubrication pump driven by two oblique gears

A speed reducer, particularly of an aircraft, includes a central sun gear mounted to rotate with a drive shaft about a rotation axis X, an annular ring gear coaxial with the X axis, and a plurality of planet gears arranged about the X axis and mounted to be movable on a planet carrier. The planet gears engages the sun gear and the annular ring gear, which extends around the planet gears. The speed reducer further includes a lubricant recovery device having a pipe for recovering lubricant discharged from the reducer by centrifuging. The recovery device has scoops mounted to pivot about a pivot axis P on a movable member of the speed reducer that rotates about the X axis between a deployed state and a rest state.

Growing community of inventors

Moissy-Cramayel, France

Emmanuel Fabrice Marie Baret