Safran Aircraft Engines

Safran Transmission Systems

Paul Ghislain Albert Levisse

Olivier Belmonte

Julien Fabien Patrick Becoulet

Emmanuel Fabrice Marie Baret

Michel Gilbert Roland Brault

Alexandre Jean-Marie Tan-Kim

Franck Emmanuel Bosco

Olivier Formica

Romain Truco

Caroline Marie Frantz

Vincent François Georges Millier

Guillaume Pierre Mouly

Pierre Jean-Baptiste Metge

Didier Gabriel Bertrand Desombre

Catherine Pikovsky

Patrice Jocelyn Francis Gedin

Amélie Argie Antoinette Chassagne

Yanis Benslama

Clément Paul René Niepceron

Pierre-Alain Jean Philippe Reigner

Claire Marie Figeureu

Fabien Roger Gaston Caty

Alexandre Corsaut

Jean-Claude Christian Taillant

Fabrice Joel Luc Chevillot

Fabrice Joël Luc Chevillot

A fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil transfer device for transferring oil between a stator and a rotor, the device including a stator ring having a cylindrical inner surface and internal oil ducts and a shaft engaged in the ring and having a cylindrical outer surface and internal oil ducts; the device includes a plain bearing located between said cylindrical inner surface and the cylindrical outer surface and defined by a single band; and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, each of these rolling bearings having one of the rings thereof integrated in one of the elements selected from the ring and the shaft.

Fan module equipped with an oil transfer device

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 turbomachine module having a longitudinal axis, having a shroudless propeller which is rotated about the longitudinal axis by a drive shaft, which is connected at least to a compressor rotor, and at least one distributor comprising a plurality of stator vanes which extend along a radial axis which is perpendicular to the longitudinal axis Z from a fixed casing, the distributor being arranged downstream of the propeller. The fixed casing can be an inter-compressor casing which is arranged downstream of a low-pressure compressor, along the longitudinal axis, the inter-compressor casing having a ring which has a longitudinal axis and which is provided with sleeves intended to support the stator vanes, the inter-compressor casing and the ring being monobloc.

Turbomachine module provided with a propeller and offset stator vanes

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.

An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.

Aircraft turbine engine with an off-axis propeller

Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage.

Aircraft turbomachine

A turbomachine having a contrarotating turbine for an aircraft, the turbomachine including a contrarotating turbine of which a first rotor is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor configured to rotate in an opposite direction of rotation and connected to a second turbine shaft. The first rotor includes turbine wheels interleaved between turbine wheels of the second rotor, the turbomachine further including a planetary-type epicyclic mechanical reduction gear which has a sun gear driven in rotation by the second shaft, a ring gear driven in rotation by the first shaft, and a planet carrier attached to a first stator casing of the turbomachine located upstream of the contrarotating turbine with respect to a direction of flow of gas in the turbomachine. The turbomachine includes bearings for guiding the first and second shafts.

Turbomachine having a contrarotating turbine for an aircraft

A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

Turbomachine module equipped with an electric machine rotor

An aircraft turbomachine having a longitudinal axis includes a high-pressure (HP) body, a low-pressure (LP) body, a fan, and a reduction gear having an epicyclic gear train. The turbomachine includes three modules: a first module having the LP turbine and the LP shaft, a second module having the LP compressor and a journal secured to the rotor of the LP compressor, and a third module having an input shaft of the reduction gear, this input shaft having an upstream end for coupling to a sun gear of the reduction gear and a downstream end comprising first splines that are oriented parallel to the axis and are configured to be engaged in second complementary splines of said second module.

Modularity of an aircraft turbomachine

Aircraft turbine engine (), comprising:—at least one first turbine rotor () connected to a first turbine shaft () and comprising rotor blades located in a stream (V),—an annular exhaust casing () supporting at least one bearing () for guiding the rotation of the first shaft and comprising arms () located in the stream, downstream of the blades, and—a mechanical planetary gearbox () which comprises a sun gear (), a ring gear () and a planet carrier (), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device () for recovering and discharging oil projected centrifugally by the reduction gear.

Recovery of lubricating oil from a reduction gear of an aircraft turbine engine

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

Disclosed is a turbomachine () with counter-rotating turbine for an aircraft, comprising: &#x2014;a high-pressure body, &#x2014;a low-pressure counter-rotating turbine (), &#x2014;a planetary-type mechanical epicyclic reduction gear (), &#x2014;a guide bearings (-) for the turbine shafts (), characterised in that said reduction gear () and certain of the bearings () are housed in a lubrication chamber () supplied with oil and comprising dynamic seals (-), and in that the turbomachine comprises circuits (C, C) for pressurising these seals.

Pressurising of lubrication chambers in a turbomachine with counter-rotating turbine

A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.

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Moissy-Cramayel, France

Paul Ghislain Albert Levisse