Snecma

Safran Aircraft Engines

Safran Transmission Systems

Herakles

Olivier Belmonte

Paul Ghislain Albert Levisse

Augustin Curlier

Emmanuel Pierre Dimitri Patsouris

Clementine Charlotte Marie Mouton

Lionel Rene Henri Weller

Vincent François Georges Millier

Thomas Julien Nguyen Van

Jean-Luc Christian Yvon Goga

Amélie Argie Antoinette Chassagne

Clémentine Charlotte Marie Mouton

Gregory Nicolas Gerald Gillant

Gilles Alain Marie Charier

Julien Fabien Patrick Becoulet

Didier Jean-Louis Yvon

Clément Paul René Niepceron

Olivier Formica

Gilles Alain Charier

Caroline Marie Frantz

Antoine Jean-Philippe Beaujard

Christophe Paul Jacquemard

Tewfik Boudebiza

Guillaume Pierre Mouly

Sebastien Jean Laurent Prestel

Alain Marc Lucien Bromann

Clément Cottet

Jean-Noel Mahieu

Thomas Langevin

Patrice Jocelyn Francis Gedin

Jean Charles Olivier Roda

Olivier Bazot

Guillaume Glemarec

Yanis Benslama

Serge Louis Antunes

Sébastien Jean Laurent Prestel

Franck Emmanuel Bosco

Jeremy Phorla Lao

Mathieu Perrier

Jérémy Phorla Lao

Lucie Galons

Lionel René Henri Weller

Stevan Le Goff

Jean-Luc Christian Goga

Gregory Nicolas Gillant

Gilles Le Gouellec

Pierre-Alain Jean Philippe Reigner

Fabien Roger Gaston Caty

Paul Rodrigues

Romain Truco

Jacques René Bart

Jean-Noël Mahieu

Stephan Aubin

Jean Noel Mahieu

Fabrice Joel Luc Chevillot

Julien Foll

Muriel Jane Sylvie Borzakian

Amadou Lamine M'Bengue

Jean-Pierre Leboulanger

Fabrice Joël Luc Chevillot

Dimitri Alain Fauron

Yann Frédéric Vincent Harnay

Ludovic Gallego

Julien Austruy

Grégory Nicolas Gérald Gillant

Xavier Millier

Stéphan Aubin

Stefan Legoff

Bruno Varone

Jean Noël Mahieu

Jean-Luc Christina Yvon Goga

Emmanuel Pierre Patsouris

Clementine Charlotte Mouton

Muriel Jane Borzakian

Lionel Rene Weller

The invention relates to a device comprising a fixed actuator for a control system for the orientation of fan blades of a turbomachine, comprising: at least one actuator body housed inside an annular casing of the turbomachine forming a bearing support, the annular casing being centred on a longitudinal axis of the turbomachine an inclined relative thereto, the actuator body having an internal volume in which a piston is able to slide, separating the internal volume into two chambers isolated from one another; and a plurality of actuator rods passing through the annular casing forming a bearing support and each having one end fixed to the piston and an opposite end intended to be connected to an internal ring of a movement transfer bearing in order to drive it in translation, the internal volume of the actuator body being closed downstream by a chamber bottom which forms a single part with the annular casing forming a bearing support.

Variable pitch fan

An unducted rectifier for a turbomachine is provided. The rectifier includes: (1) stator vanes each having a root and a blade radially projecting from the root, the root having two half-platforms; (2) pivots, each associated with a vane mounted so as to pivot about a pitch axis and configured to connect to a system for changing the pitch of the blades, each pivot having an upper platform and a cylindrical lower portion; and (3) attachment systems for attaching the half-platforms of the root of the vane to the associated pivot, each having two plates having a substantially identical shape to each half-platform and a clamping system for clamping the half-platforms between the plates of the attachment system and the upper platform of the pivot.

Unducted rectifier for a turbomachine, turbomachine module and aircraft turbomachine

A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Fan module provided with an oil transfer device

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

The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clamping.

Radial locking of a blade pivot with adjustable orientation for a turbomachine fan hub

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

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

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

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.

Turbine rotor wheel for an aircraft turbomachine

A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.

Turbomachine with counter-rotating turbine for an aircraft

The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Blade pivot with adjustable orientation and protected integrity for a turbomachine fan hub

A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

Blade pivot of adjustable orientation and of reduced bulk for a turbomachine fan hub

Aircraft turbomachine with mechanical reducer and counter-rotating turbine are described. The turbomachine includes a fan driven in rotation by a fan shaft, a mechanical reducer with epicyclic gear train, a gas generator comprising a counter-rotating turbine, a first turbine shaft of which is coupled to an input shaft of the reducer and to a pin, and a second turbine shaft of which is coupled to the fan shaft. The guidance of the reducer input shaft is provided by a first ball bearing, the guidance of the pin is provided by a second roller bearing, and the guidance of the first shaft is provided by a third roller bearing axially interposed between the first and second bearings.

Aircraft turbomachine with mechanical reducer and contrarotative turbine

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Perthes en Gatinais, France

Olivier Belmonte