Snecma

Safran Aircraft Engines

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Ge Aviation Systems Limited

Aircelle Limited

Gilles Alain Charier

Wouter Balk

Tewfik Boudebiza

Francois Gallet

Nathalie Nowakowski

Kevin Morgane Lemarchand

Augustin Curlier

Didier Rene Andre Escure

Jean-Louis Picard

Olivier Belmonte

Bruno Albert Beutin

Antoine Jean-Philippe Beaujard

Regis Eugene Henri Servant

Régis Eugène Henri Servant

Serge Rene Morreale

Daniel Georges Plona

Laurent Soulat

Pierre-Alain Jean Philippe Reigner

Marc R Marchi

Serge René Morreale

Jonathan Evert Vlastuin

Nicolas Joseph Sirvin

Philippe Pierre Vincent Bouiller

Augustin Marc Michel Curlier

Patrick Charles Georges Morel

Nicolas Dezeustre

Gerard Philippe Gauthier

Didier René André Escure

Philippe Pierre Bouiller

Thomas Julien Nguyen Van

Eric Stephan Bil

Herve Hurlin

Nicolas Alain Bader

Philippe Gerard Chanez

Laurent Gille

Christian Sylvain Vessot

Didier Fabre

Jean Pierre Mareix

Sebastien Emile Philippe Tajan

François Gallet

Christopher Roy Carrington

Guy Dusserre-Telmon

Philippe Jacques Pierre Fessou

Henri Yesilcimen

Denis Louis Bocquet

Adrien Pierre Jean Pertat

Patrice Rosset

Zoltan Zsiga

Stéphane Rousselin

Gilles Louis Rollin

Julien Michel Patrick Christian Austruy

Pascal Lejeune

Nadege Hugon

Jean-Christophe Duffet

Nicolas Maurice Herve Aussedat

Aleksander Krzysztof Szymandera

Jean-Pierre Mourlan

Jan Sikorski

Xavier Jean-Michel Andr&eacute; Guyonnet

Jean-François Endy Bersot

Jean-Louis Bertrand

Didier Escure

Frederic Guihard

Caroline Marie Franz

Kévin Morgane Lemarchand

Mathieu Lallia

Lionel Jean Leon Lefranc

Ludovic Michael Laurent Toupet

Xavier Ja Guyonnet

Jean Philippe Pierre-Alain Reigner

Xavier, J Guyonnet

Marek Malitka

Pascal Le Jeune

Didier Rene Escure

Julien Michel Austruy

Aleksander Szymandera

Nicolas Jerôme Jean Tantot

Gérard Philippe Gauthier

The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY') offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

Aircraft propulsion assembly equipped with a main fan and with a least one offset fan

An aircraft including a fuselage, a lateral support wing () and a propulsion assembly () mounted under the wing. The wing includes at least two structural spars () extending from the fuselage toward the tip of the wing, one of these () being upstream and the other () downstream. The propulsion assembly includes a gas generator () and at least two offset fans () arranged on either side of the axis of the gas generator. The offset fans () are attached directly to one of the spars () and the gas generator () is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (&#x3b1;) with the axis of the fuselage. The two offset fans () are axially offset from one another.

Aircraft with multiple fan propulsion assembly fixed under the wing

A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.

System for changing the pitch of a turboprop engine comprising an upstream pair of contrarotating propellers

An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Aircraft propulsion assembly equipped with a main fan and with at least one offset fan

An aircraft includes a wing having a first upstream spar and a second downstream spar extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream spar via at least one first and second fastener.

Aircraft with a propulsion unit with offset fan

Engine comprising a propeller unit with a pair of contrarotating propellers (), a gas generator () supplying a power turbine (), the pair of propellers being rotationally driven by the shaft (A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset () and a first stage () comprising a simple gearset connecting the turbine shaft (A) and the differential gearset (), the engine air intake comprising an air intake duct (), the air intake duct () being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset ().

Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.

Turbo-engine including two separate ventilation flows

An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Epicyclic reduction device for the rotational drive of blade sets of a reduction turbomachine

A system, including: a linear actuator axially arranged in a first propeller and rotatably secured thereto, a first linking mechanism connecting a rod of the linear actuator to a second propeller to change a setting of blades thereof, and including an intermediate bearing between the propellers, which is capable of transmitting translation of the rod of the linear actuator and disconnecting a rotatable link to the first propeller to make it possible to change the setting of the blades of the second propeller rotated in an opposite direction to the first propeller, and a second linking mechanism combined with blades of the first propeller to change a setting thereof.

System for changing the pitch of the contra-rotating propellers of a turboshaft engine

The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream () and downstream (), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterized in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing () of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator () in the stationary reference frame with an element () that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected to a rotating casing () of the downstream propeller, and a movement-transmission mechanism () connecting said movable element of the linear actuator to the blades, comprising a load-transfer bearing arranged to transmit the axial forces from the linear actuator to the rotating reference frame of the downstream propeller.

Propulsion unit with a pair of propellers for an aircraft

The epicyclic reduction gear comprises a planetary input shaft, planet gears meshing around said shaft and supported by a planet carrier, and two transverse sides. According to the invention, the reduction gear comprises at least one fluid transfer pipe suitable for being connected to a fluid supply source and passing through the planet carrier, being linked in rotation to same, from a first of said transverse sides of the reduction gear to a second of said transverse sides of the latter in order to open on the outside of the reduction gear and dispense the fluid.

Epicyclic reduction gear with fluid transfer pipes, and propeller turbomachine for an aircraft with such a reduction gear

A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to the propeller, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller

A device for supplying oil under pressure to a linear actuator of a turbine engine, in which the actuator includes an internal fixed portion and an external movable portion and a regulating device for regulating and supplying oil to chambers of the actuator, is provided. The regulating device is mounted radially outside the movable portion of the actuator, and the fixed portion of the actuator includes on its upstream end portion oil passage channels of which the outlets open radially outwards. The device further includes an oil distribution ring which is mounted on the upstream end portion of the fixed portion and which includes internal conduits of which the inlets communicate with the outlets of the channels of the fixed portion and the outlets open axially downstream and are connected to the regulating device.

Device for supplying oil under pressure to a linear actuator of a turbine engine

The invention relates to a fixed turbine engine receiver part comprising a fixed hollow shaft for carrying ancillary systems of a turbine engine, centered on the turbine engine axis, turbine engine ancillary systems, an assembly for holding ancillary systems in position situated inside the fixed hollow shaft. The assembly for holding ancillary systems in position comprises at least one first ancillary system support ring, having an axis substantially parallel with the turbine engine axis, a first distance sleeve for holding the first ancillary system support ring in position, having an axis substantially parallel with the turbine engine axis, the first distance sleeve bearing against the first support ring, such that the first support ring comprises a plurality of mutually separated through holes, each through hole defining a passage for at least one ancillary system, each through hole being traversed by at least one of the ancillary systems of the turbine engine.

Fixed turbine engine receiver part comprising an assembly for holding ancillary systems in position inside a fixed hollow shaft

A device can be housed coaxially inside a sleeve in which the supplies are situated, and includes: a hollow cylindrical body that fits inside the sleeve and accepts the mechanism in the housing of the hollow body, with passages for respectively connecting the supplies to said mechanism; and a cover which is integrated or fixed, removably, on the front side of the cylindrical body and connects the hidden supplies to the respective passages of the body.

Device for the blind coupling of fluidic, electrical or similar supplies, to a receiving control mechanism

Growing community of inventors

La Grande Paroisse, France

Gilles Alain Charier