Safran Transmission Systems

Safran Aircraft Engines

Safran Electrical & Power

Hispano Suiza

Guillaume Julien Beck

Adrien Louis Simon

Boris Pierre Marcel Morelli

Guillaume Pierre Mouly

Jordane Peltier

Jordane Emile André Peltier

Jean-Pierre Serey

Patrice Jocelyn Francis Gedin

Boris Morelli

Benjamin Feraud

Simon Loic Clement Lefebvre

Quentin Pierre Henri Pigott

Stéphane Prunera-Usach

Mathieu Jean Jacques Santin

Aldric Renaud Gabriel Marie Moreau De Lizoreux

Jean-Michel Bernard Paul Chastagnier

Patrice Gedin

Jean-Charles Michel Pierre Di Giovanni

Alexis Claude Michel Dombek

Antoine Jacques Marie Pennacino

Mathieu Jean Charrier

Samuel Raymond Germain Becquerelle

Balint Pap

Simon Loïc Clément Lefebvre

Bálint Pap

Julie Lemoine

Thomas Turchi

Loïc Francois

Patrice Julien Ptaszynski

Dhafer Ghribi

Alexis Dombek

Antoine Mathieu

Yohan Douy

Jérémy David Seban

Maxime Amiet

Cécile Bruot

Aissa Benykhlef

Pauline Marie Cécile Autran

Jean Clayette

Pauline Marie Cecille Autran

An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Aircraft turbomachine with mechanical reduction gear

A sun gear for a mechanical gearbox of an aircraft turbomachine, the sun gear having an annular shape around an axis and including an internal annular part having at its internal periphery coupling grooves, an external annular part having at its external periphery at least one meshing tooth, the external part extending around the internal part, and an annular veil connecting the internal and external parts. At least one of the internal and external parts can include two independent rings, each having grooves or teeth, and the veil can have two annular branches connected respectively to the two rings.

Sun gear for a mechanical reduction gear of an aircraft turbomachine

A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.

Planet carrier for a speed reducer on an aircraft turbomachine

A pre-assembly method for an aircraft turbomachine, including preliminarily assembling, outside the turbomachine, the following components with each other: a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of the at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of the at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.

Pre-assembly method for an aircraft turbomachine

A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element.

Power transmission module for an aircraft turbomachine

A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.

Mechanical reduction gear for an aircraft turbomachine

A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.

Mechanical gearbox for aircraft turbomachine

A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.

Mechanical reduction gear for aircraft turbomachine

A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Aircraft propulsion assembly provided with a rotary transformer for supplying the blades with electrical energy

An impeller () for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means () for supporting axes of rotation of planets of said reducer, said impeller comprising means for lubricating teeth of said planets and bearings of said axes, said lubrication means comprising an annular groove () located on the internal periphery of said impeller and opening radially towards the inside, said groove being connected to lubricant supply and/or spray means, characterised in that the impeller comprises dynamic annular sealing means () located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator () of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.

Impeller for a planet carrier of a planetary gear speed reducer of a turbomachine

A speed-reducing unit, particularly for transferring torque between a gas turbine and a fan in a turbine engine, includes an annular ring, at least one gear that is coupled to the ring, the ring including two annular half-rings that are offset relative to each other along the main axis of the speed-reducing unit and that are coupled with at least one gear, and a plate for supporting the two half-rings, in relation to which the two half-rings are rotationally fixed about the main axis of the speed-reducing unit. Each half-ring includes an internal helical tooth. Each half-ring is connected to the support plate so as to be able to be uncoupled from at least one gear when at least one gear exerts a disengaging action on each half-ring, with the amplitude of the action being greater than a determined amplitude value.

Disengageable speed-reducing unit

The invention relates to a method for assembling (S) a planet carrier (), comprising the following steps: separately producing (S) the cage () and the cage carrier (), providing a machining allowance at one element from among the through-holes () in at least one upright () of the cage () or the through-hole () in a finger bar () of the cage carrier (), and/or at one element from among a bearing seat () or a rolling bearing seat (); assembling (S) the cage () and the cage carrier () and securing (S) same to produce a one-piece assembly; determining (S) the position of a reference axis (Y, Y) linked to the cage (), to the cage carrier () and/or to the shaft (); and, taking account of the position of the reference axis (Y, Y), machining (S) all or part of the machining allowances.

Method of assembling a planet carrier

In an aeroengine comprising a gas turbine engine driving a propeller via a reduction gearbox, the propeller comprising a plurality of blades, each provided with one or more electrical deicer elements and being set into rotation by a propeller-carrying shaft passing through the gearbox, the propeller-carrying shaft having a fastener flange for fastening to the propeller, provision is made, in order to deliver the electrical power needed for powering said electrical deicer elements, for the aeroengine to include a rotary three-phase transformer set into rotation by the propeller-carrying shaft and comprising firstly a rotor mounted inside the propeller-carrying shaft and angularly secured thereto, and secondly a stator secured to a stationary portion of the aeroengine, the rotary three-phase transformer being arranged behind the propeller fastener flange.

Turbine engine having a three-phase transformer for powering electrical deicer elements

An assembly for an epicyclic reduction gearset, including a satellite carrier, satellites, and at least one satellite bearing including a central axis linked to the satellite carrier. An inner ring mounted on the central axis, an outer ring mounted to rotate around the central axis. A lubrication circuit brings a flow of oil between the rings. The lubrication circuit includes a first portion supplied with oil with openings to the outside of the inner ring in a radially inner area of the bearing. A second portion has openings to the outside of the inner ring. An intermediate portion has at least one channeling connecting the first portion to the second portion, having at least one singular pressure reduction formed by an elbow and at least one flattening of a transverse cross-section. The central axis has a radially outer first surface. The inner ring has a radially inner second surface.

Assembly for an epicyclic reduction gearset comprising at least one satellite bearing comprising lubrication means

Growing community of inventors

Moissy-Cramayel, France

Guillaume Julien Beck