Safran Aircraft Engines

Snecma

Snecma Moteurs

Marc Patrick Tesniere

Antoine Elie Hellegouarch

Philippe Loewenstein

Sebastien Dron

Bruno Albert Beutin

Guillaume Lefort

Thibaud Jean-Baptiste Guibert

Felix Pasquer

Gilles Lucien Fontenoy

Tewfik Boudebiza

Christian Sylvain Vessot

Quentin Matthias Emmanuel Garnaud

Nicolas Marc Florent

Jean-Loic Herve Lecordix

Maryline Emmanuelle Besnard

Gabriela Philippart

Mario Antoine Lambey

Stephane Jacques Francois Thomas

Frederic Paul Eichstadt

Thibaut Guibert

Gregory Prudhomme

Lydie Marie Helene Chevalier

Gabriel Noirclerc

Frédéric Darcy

Félix Pasquer

Lydie Marie Chevalier

Jean-Baptiste Guibert Thibaud

Sébastien Dron

Lydie Marie Hélène Chevalier

An engine assembly for an aircraft including a bypass turbomachine as well as a turbomachine attachment pylon including an air-oil exchanger system arranged in an inter-ducts compartment between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling, the exchanger system being supplied with air from a secondary flow duct of the turbomachine delimited radially on the inside by the inter-ducts cowling, and the exchanger system being supported by a support arranged in the inter-ducts compartment, this support being mechanically connected to the attachment pylon by connecting means passing through the inter-ducts cowling.

Engine assembly for an aircraft having an air-oil exchanger system support with optimized attachment

A load-bearing structure is configured to be mounted on an engine core of a turbofan engine. The load-bearing structure comprises two longitudinal beams and a transverse connection connecting them. Each of the longitudinal beams comprises a forward mounting interface and a rear mounting interface for mounting the structure on the engine core while allowing at least the longitudinal travel of the engine core. Each longitudinal beam also comprises a lateral suspension point for transmitting longitudinal and vertical forces between the load-bearing structure and a suspension structure. The load-bearing structure further comprises a transverse connection comprising a central suspension point for transmitting lateral and vertical forces between the load-bearing structure and the suspension structure.

Load-bearing structure intended to be mounted on a gas generator

The invention concerns a suspension device () for a turbomachine comprising a body () intended to be fixed to a fixed part of an aircraft, extending along a longitudinal axis (A) intended to be parallel to a driving shaft axis of the turbomachine once the suspension device () is connected to the turbomachine, a first connecting rod () and a second connecting rod () located in the same transverse plane (P) perpendicular to the longitudinal axis (A) of the body, each comprising a first end articulated with respect to the body (), and a second end intended to be articulated to a first part of the turbomachine, a third connecting rod () articulated on the body () between the first ends of the first and second connecting rods () and intended to be articulated on a first part of the turbomachine between the second ends of the first and second connecting rods (), the suspension device () being characterised in that it further comprises a rudder () articulated on the body () and a fourth connecting rod () and a fifth connecting rod () each extending along an axis of extension (L, L) and each comprising a first end () articulated on the rudder () and a second end () intended to be articulated on a second part of the turbomachine.

Suspension device

The invention relates to the field of fairings of aircraft propulsion units, and more particularly to an assembly comprising a longitudinal beam () configured to be mounted on a lateral of a turbofan () engine core (), oriented parallel to a longitudinal axis (X) of the turbofan (), an opening fairing () cowl () of the engine core () and a deployment mechanism () mounted on the longitudinal beam () to move the opening cowl () between an open position and a closed position.

Opening cowl assembly and deployment mechanism

Propulsion assembly comprising a duct for feeding the gas generator in an inter-duct casing

An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.

Assembly between an aircraft pylon and a turbine engine

The ball joint device () for suspending a turbine engine from a strut or suspending equipment on the body of a turbine engine. Said device comprises a first member (), one end of which carries a ball joint () and is interposed between the two lugs () of a second member (), the ball joint comprising a bore () for the passage of a shaft (), the ends of which shaft pass through openings () in the lugs. A first () of the lugs comprises or carries first means for axially holding the shaft on the side opposite the ball joint, which means comprise a cover ('), and a second () of the lugs comprises or carries second means () for axially holding the shaft on the side opposite the ball joint. The device further comprises a resilient member (&#x2032;) that is deformable under compression and is held by the cover, said resilient member (&#x2032;) being designed to bias a support element (), through which the shaft passes and which is in axial abutment on the ball joint (), axially in a direction away from the cover.

Ball joint device for a turbine engine

A suspension device for suspending, for example, a turbine engine to a pylon, the device comprising a first unit interposed between a first lug and a second lug of a second unit, the first unit having a bore for passing an axle running through first and second bushings mounted respectively in said first and second lugs; and a clamping unit interacting with the axle. The device further comprising a third bushing mounted in the second lug and having radial centering means which interact with the complementary centering means of a head section of the axle; and a fourth axially slidably mounted bushing, biased axially by the clamping unit, and comprising radial centering means which interact with complementary centering means of the first bushing.

Turbine engine suspension device

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

An aircraft propulsion engine including a fan case, and a cowl forming part of the nacelle of the engine and being designed to at least partially surround the case leaving a space between the cowl and the case, in which space at least one piece of equipment is mounted and extends along the axis of the engine, is provided. The cowl includes a wall and wall stiffeners fixed to the internal face of the wall. At least a part of the stiffeners of the cowl is arranged to form air guide ducts, the air guide ducts being assembled into an air distribution circuit to ventilate the equipment.

Engine cowl incorporating an equipment ventilation circuit

An aircraft provided with turbojet engines of which the nacelles are partially embedded in the fuselage of the aircraft is disclosed. The aircraft includes an internal space at engine nacelles. The internal space includes a platform capable of supporting personnel and maintenance equipment, with the portions of the nacelles located inside the aircraft comprising trapdoors or devices for accessing inside the engines from the platform.

Aircraft with reciprocating engines partially embedded in the fuselage

A suspension for suspending of a turbine engine from the structure of an aircraft using a beam with an attachment device which attaches to the structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine is disclosed. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders.

Suspension for suspending a turbine engine from the structure of an aircraft

An integrated propulsive turbofan engine system includes a downstream cylindrical nacelle structure in two parts. The first of the two parts is fixed and fastens engine attachment elements and an intermediate casing to the aircraft. The second of the two parts may move between a closed position used during operation and an open position during maintenance when access to engine components is needed.

Integrated propulsive system comprising a bypass turbojet engine

A propulsion system for an airplane having an integrated pylon includes a bypass turbojet and a nacelle. The nacelle has a downstream cylindrical part which is rigid and is attached at its upstream end to an intermediate case of the engine. This downstream cylindrical part also includes a longitudinal beam for attaching rods to secure the engine to the airplane.

Propulsion system with integrated pylon

A suspension for suspending a turbine engine from the structure of an aircraft is disclosed. The suspension includes a beam with a first element including a first attachment unit which attaches the beam to the structure and a second element including a second attachment unit which attaches to the beam to the turbine engine. The beam further includes a first plate and a second plate. The plates are positioned transversely to the axis of the engine and joined together by a layer of elastomer. The first plate being secured to the first element and the second plate to the second element. This arrangement allows vibration damping between the engine and the structure of the aircraft.

Growing community of inventors

Champcueil, France

Marc Patrick Tesniere