Safran Aircraft Engines

Safran Nacelles

Antoine Elie Hellegouarch

Marc Patrick Tesniere

Quentin Matthias Emmanuel Garnaud

Pierre Caruel

Patrick Boileau

Olivier Kerbler

Emmanuel Pierre Dimitri Patsouris

Nicolas Joseph Sirvin

Clementine Charlotte Marie Mouton

Romain Jean-Claude Ferrier

Gina Ferrier

Alexis Heau

Nora El Ghannam

Frédéric Paul Eichstadt

Quentin Garnaud

Frederic Paul Eichstadt

Mathieu Lerouvreur

Sébastien Michel Thierry Guillemant

Thomas Gerard Daniel Riviere

Martial Alexandre Monseu

An air inlet duct or a nacelle of an aircraft propulsion assembly includes an annular body and an annular air inlet lip with two coaxial annular walls, inner and outer, respectively. The inner wall defining a portion of an inner annular surface of the air inlet duct and the outer wall defining a portion of an outer annular surface of the air inlet duct. A control system translates the lip from a first position, in which the lip is attached to the body, to a second position, in which the lip is axially separated from the body. An annular row of grilles is translatably secured to the lip. The grilles are housed inside the body in the first position and extended from the body in order for an air flow entering the air inlet duct to pass therethrough in the second position.

Air inlet duct for a nacelle of an aircraft propulsion assembly

The invention concerns a suspension system () for a turbomachine, comprising a beam () intended to be attached to a pylon of an aircraft, and a cylindrical part () articulated on a ball joint housing, the ball joint housing comprising a body (), and a ball joint nut () articulated on the body (), the cylindrical part () being mounted so as to pivot about its axis in the ball joint nut, characterized in that the cylindrical part () is intended to be integral with a fixed part () of the turbomachine (), the body () of the ball joint housing being integral with the beam ().

Suspension assembly for a turbine engine

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

An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.

Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine

A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.

Turbojet engine nacelle including a single movable frame of a cascade thrust reverser and passages of ancillaries

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

A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.

Propulsion unit including lifting points disposed on thrust reverser cylinder supports

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

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 invention relates to a cradle () for an aircraft turbopropeller engine () of a substantially axial orientation, comprising a front arch () and a rear arch () extending transversely relative to said axial direction (A), said arches () being open at their lower ends and connected to each other by at least one axial longeron () extending between said arches (), characterised in that the longeron () is arranged in an upper portion of the cradle () and is formed in a single piece with the front arch ().

Cradle for a turbopropeller engine with integrated air inlet duct

The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon () and a rudder bar (). One part (') of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (). The system also comprises a torque bar () which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (B) of elongation of the torque bar, the opposing ends () of said bar being secured on each side of the above-mentioned part of the rudder bar.

Growing community of inventors

Moissy-Cramayel, France

Antoine Elie Hellegouarch