Safran Aircraft Engines

Snecma

Safran Transmission Systems

Emmanuel Pierre Dimitri Patsouris

Olivier Belmonte

Clementine Charlotte Marie Mouton

Arnaud Nicolas Negri

Thomas Julien Nguyen Van

Gilles Alain Marie Charier

Julien Fabien Patrick Becoulet

Romain Guillaume Cuvillier

Didier Jean-Louis Yvon

Régis Eugène Henri Servant

Guillaume Patrice Kubiak

Sébastien Emile Philippe Tajan

Sebastien Emile Philippe Tajan

Michel Gilbert Roland Brault

Christophe Paul Jacquemard

Nathalie Nowakowski

Tewfik Boudebiza

Antoine Elie Hellegouarch

Nils Edouard Romain Bordoni

Quentin Matthias Emmanuel Garnaud

Clémentine Charlotte Marie Mouton

Pierre-Alain Jean Philippe Reigner

Simon Loïc Clément Lefebvre

Jeremy Phorla Lao

Fabrice Joel Luc Chevillot

Jérémy Phorla Lao

Martial Alexandre Monseu

Fabrice Joël Luc Chevillot

An impeller () for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity () situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall () closing the cavity () in the radial direction, and the impeller includes an annular port () that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.

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

A reducing assembly includes a planet carrier that is flexible and fixed, borne by a casing which surrounds it by two distinct connections with this casing, with a device for applying a torsional prestress to the planet carrier between these two connections. Prestressing the flexible planet carrier makes it possible to limit its level of mechanical stress when it is in service, in order to simplify its design and dimensioning.

Planetary reducing gearset comprising a prestressed flexible support

A turbine engine including: a rotor having at least one variable-pitch blade which is guided to rotate on bearings relative to a fixed structure; a system for controlling the pitch of the at least one blade, the control system being rigidly secured to the rotor and including a first actuator driven by energy, and the control system further being disposed axially upstream of the bearings; a device for transferring the energy, which is disposed axially between the bearings, the transfer device including a stationary element and a mobile element; wherein the rotor is annular and delimits an inner space which is open towards the upstream side and inside of which the control system is disposed.

Turbine engine comprising a rotor with variable-pitch blades

A turbine engine including: a rotor supporting a blade and guided by means of bearings; a control system for controlling the blade, which is solidly connected to the rotor and which includes an actuator driven by energy, the control system being disposed axially upstream of the bearings; and a device for transferring the energy, disposed axially between the bearings and including a stationary member and a moving member. The rotor includes a support ring supporting the blade and a shaft having a frustoconical portion and a cylindrical portion on which the bearings and the moving member are mounted, the frustoconical portion extending about the cylindrical portion.

Turbine engine comprising a rotor supporting variable-pitch blades

A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Radial shaft device for controlling the pitch of fan blades of a turbine engine having an un-ducted fan

The turbojet includes, linking two of its parts as a main nacelle portion and a rear nacelle portion, a device which moves them relative to one another, for example in order to open a reverse gas thrust slot. The device includes a sleeve and two rods which are coaxial connected together by two screw links and two locking devices which may be engaged independently, such that the deployment of one of the rods results in the opening of the slot and the movement of the other rod, controlled by the same device, only occurs under specific turbojet maintenance circumstances.

Turbojet equipped with a double-action actuator, which can be used to control reverse thrust

The invention concerns a power transmission system of a turbomachine, comprising: According to the invention, the recovery chamber is provided with an inlet opening () directed radially outwardly and defined in a plane radially lower than a plane where an outlet port () of the ejection means is defined.

Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system

A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet including a gas generator, a first unducted propeller connected to a shaft of the gas generator via first reduction gearing, and a second unducted propeller connected to a shaft of the gas generator via second reduction gearing, wherein the first propeller and the first reduction gearing are mounted at the front of the gas generator, and wherein the second propeller and the second reduction gearing are mounted at the rear of the gas generator.

Turbojet of the unducted rotor type

A system for controlling the pitch of fan blades of a turbine engine propeller, the system including an actuator secured to a casing of the turbine engine, having a movable portion that is movable in translation relative to the casing, the movable portion being mechanically coupled to a load transfer bearing having an outer ring that is coupled to fan blade pivots so that a movement in translation of the movable portion of the actuator leads to a change in the pitch angle of the fan blades, and at least one locking peg secured to the casing of the turbine engine and suitable, in the event of the actuator malfunctioning, for mechanically locking the load transfer bearing in a position wherein the fan blades are feathered.

System for controlling the pitch of fan blades of a turbine engine, the system having a feathering-locking peg

A fan of a turbine engine includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20&#xb0;.

Low-pitch variable-setting fan of a turbine engine

A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.

Variable pitch blade pivot for a turbine engine fan hub

A device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller, the device including an actuator having at least one movable portion designed to be coupled to pivots of the fan blades of the propeller in order to modify their pitch angle when it slides, a movable part having first mechanical device suitable for co-operating with the actuator when in a fan blade pitch-unlocking position in order to enable the actuator movable portion to slide over an extended actuator stroke; and second mechanical device suitable for co-operating with the actuator when in a fan blade pitch-locking position in order to enable the actuator movable portion to slide over an actuator stroke that is shorter than the extended actuator stroke, and an actuator.

Device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller

An assembly for a turbomachine including a shaft of a rotor of a turbomachine, and at least two bearings allowing at least one portion of the shaft to be supported, including a bearing support configured to be connected to a casing of the turbomachine which extends between the internal rings of the bearings while being mounted thereon, as well as a bearing connector which is connected to the shaft of the rotor and which is mounted on the external rings of the bearings while extending between them, the bearing support and the bearing connector being common to the two bearings and delimiting together at least partially an oil circulation housing common to the two bearings.

Assembly consisting of a bearing support and bearings of a rotor shaft in a turbomachine

A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.

Lever arm device for controlling the pitch of fan blades of a turbine engine having an unducted fan

A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, is disclosed. The shaft includes an external portion that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade in order to adjust its pitch, and an internal portion, independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing in order to pivot the shaft about a radial axis, and to close an oil enclosure in which the bearing is housed, the external and internal portions of the shaft being coupled to each other. A method of mounting such a shaft and a control device including such a shaft are also disclosed.

Radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, and a method of mounting such a shaft

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Moissy-Cramayel, France

Emmanuel Pierre Dimitri Patsouris