Snecma

Safran Aircraft Engines

Snecma Moteurs

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

Safran Nacelles

Other

Aircelle Limited

Institut Superieur De L'aeronautique Et De L'espace

Bruno Albert Beutin

Jeremy Edmond Fert

Jacques Rene Bart

Carmen Gina Ancuta

Bruna Manuela Ramos

Antoine Olivier Francois Colin

Nuria Llamas Castro

Patrick Boileau

Marc Patrick Tesniere

Didier Jean-Louis Yvon

Christian Sylvain Vessot

Jacky Raphael Michel Derenes

Maria Natal

Monique A Thore

Clarisse Savine Mathilde Reaux

Pierre Caruel

Michel Gilbert Roland Brault

Gilles Alain Charier

Nathalie Nowakowski

Jean-Louis Charbonnel

Georges Mazeaud

Kevin Morgane Lemarchand

Nicolas Joseph Sirvin

Alexandre Alfred Gaston Vuillemin

Guillaume Glemarec

Philippe Pierre Bouiller

Philippe Gérard Chanez

Nicolas Alain Bader

Philippe Gerard Chanez

Jean-Louis Picard

Patrick Charles Georges Morel

Hervé Jean Albert Mouton

Patrick Gonidec

Jean-Marie N Pincemin

Mathieu Patrick Jean-Louis Lallia

Frederic Paul Eichstadt

Michel G Hugues

Jacques René Bart

Andre C Collot

Michel Gilbert Brault

Gilles Claude Massot

Christophe J Thorel

Daniel J Martin

Philippe Fessou

Yann Lebret

Valerio Capasso

Fabienne Lacorre

Alexis Pereira

Nicolas Maurice Herve Aussedat

Jean-Baptiste Manuel Nicolas Vignes

Frédéric Paul Eichstadt

Jeremy Fert

Nelson Dos Santos

Claude Dejaune

Lambert Olivier Marie Demoulin

Francis Georges Garnier

Carole Claudine Touron

Miguel Angel Aguirre

Antoine Olivier François Colin

Zoltan Zsiga

Pascal Gérard Gervais

Pascal No&euml;l Brossier

Sébastien Duplaa

Mario Antoine Lambey

Jean-Claude Gregoire

Alain Espenel

Bernard Robic

Herve Paitre

Jean-Francois Ranvier

Monique Andrée Thore

Nicolas Tantot

Patrick Charles Morel

Joel Creti

Mathieu Lallia

Lionel Jean Leon Lefranc

Ludovic Michael Laurent Toupet

Mario Lambey

Eric Landre

Didier Yvon

Fabien Burdin

Elisabeth Guigli

Michel Fran&ccedil;ois Raymond Franchet

Jean-Lo&iuml;c Herv&eacute; Lecordix

Marc Georges Loubet

Claude P Maignan

Jean-Loic H Lecordix

Jean-Pierre Donnadieu

Gerard M Vennin

Pascal Gervais

Jacky Raphaël Michel Derenes

Marc Tesnière

Jérémy Fert

Anthony Pierre Guy Delaforge

Pascal Gerard Gervais

Monique Andree Thore

A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.

Structure for linking and supporting a turbine engine on an aircraft pylon

A support assembly for supporting a main accessory gearbox of an aircraft turbine engine, the accessory gearbox including gears and supporting at least one item of equipment driven by the gears. The support assembly can include a structure for connecting and supporting the turbine engine to a pylon of the aircraft including: an intermediate axial portion for attachment to the pylon, having an upper end that defines a linking interface with the pylon, the intermediate axial portion bearing suspension rods, which are intended to be connected to the turbine engine; a front axial portion extending forward of the intermediate portion and having at least one suspension member configured to be connected to the turbine engine; and a rear axial portion extending rearwards of the intermediate portion and supporting the main accessory gearbox.

Assembly for supporting an accessory gearbox of an aircraft turbine engine

An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

Aircraft with an offset nacelle aligned with the wake of the wing

A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

Drive unit for an aircraft having lifting points, and carriages for supporting such a unit

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

An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.

Propulsion assembly for an aircraft, comprising a gas generator, two offset fans and an air inlet sleeve

The main purpose of the invention is an air circulation device () for a turbomachine (), comprising an air conveyance circuit () adapted to bring hot bleed air (A) from the turbomachine () to a part to be heated (), comprising a first segment fixed in rotation to a rotating part () and comprising at least one hot air (A) conveyance conduit (), and a hot air passage device (), comprising an annular compartment fixed in rotation to the first segment, characterise in that the annular compartment comprises a heat exchanger in contact with external air, and in that the hot air passage device () comprises a hot air bypass system to deviate air entering into the device and to make it circulate along the heat exchanger when the temperature of this intake air is above a predetermined threshold.

Air circulation device for a turbomachine comprising a hot air bypass system to a heat exchanger

The invention relates to a method for mounting an engine () on an aircraft strut () comprising engine suspension members () integral with the strut, the engine being integral with a suspension cradle () whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part () is fixed to the strut beforehand, by attaching it to said suspension members (), said intermediate part () having an interface intended to cooperate with a complementary interface provided on the cradle (), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.

Method and device for mounting an engine on an aircraft pylon

A propulsive wing of an aircraft including at least two structural spars, upstream and downstream that extend in a wing span direction of the wing. A propulsion assembly includes at least two fans that are each driven by at least one gas generator. The at least one gas generator extends along an axis that is remote from the axis of rotation of at least one fan. At least one of the spars includes a first part and a second part between which the propulsion assembly is arranged. The first and second parts are interconnected by a rigid structure that is shaped to extend at least in part around the fans. The propulsion assembly is supported by the rigid structure.

Propulsive wing of an aircraft

An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing, second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall.

Unducted propeller turboshaft engine provided with a reinforcing shell integrating pipe segments

A turbine engine having a nacelle is provided. The nacelle includes, upstream, an air intake fairing and an element for deflecting foreign objects which defines with the fairing an air intake flow path for supplying air to two coaxial flow paths which are a radially inner flow path and a radially outer flow path. The outer flow path being is by a hub housing and scoops, the hub housing and the scoops being installed downstream of the element for deflecting objects. Each scoop includes two independent portions which are an upstream portion borne by the hub housing, and a downstream portion borne by the nacelle.

Turbine engine having an element for deflecting foreign objects

A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms.

V-shaped gearbox for driving turbomachine equipment

Aircraft turbomachine comprising at least one heat exchanger () and a gearbox () in a V-shaped overall configuration and comprising two lateral arms () joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.

Electroformed nickel-chromium alloy

The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.

Propulsion unit for an aircraft

A turbine engine for aircraft includes a gas generator as well as to a receiver driven by a power turbine, and to an electric power generator, the rotor of which centered on a rotor axis distinct from the longitudinal axis, is driven into rotation by the power turbine, via a mechanical gear transmission, including a toothed drive wheel centered on the axis. Further the receiver includes a first propeller driven by a free power turbine and the toothed drive wheel is attached on an outer case of this power turbine.

Turbine engine with a power turbine equipped with an electric power generator

Growing community of inventors

Evry, France

Bruno Albert Beutin