Safran Aircraft Engines

Quentin Matthias Emmanuel Garnaud

Antoine Elie Hellegouarch

Guillaume Glemarec

Marc Patrick Tesniere

Emmanuel Pierre Dimitri Patsouris

Nicolas Joseph Sirvin

Guilhem Seize

Clementine Charlotte Marie Mouton

Frédéric Dautreppe

Hervé Jean Albert Mouton

Frédéric Paul Eichstadt

Martial Alexandre Monseu

Benoit Bernard René Leclerc

A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.

Turbojet engine fan casing

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 relates to a turbomachine () extending along an axis (X), comprising a high-pressure body with a high-pressure compressor () coupled in rotation to a high-pressure turbine (), and a low-pressure body including a low-pressure compressor () coupled in rotation to a low-pressure turbine (), an upstream casing () located upstream of the high-pressure compressor (), and means of suspension () for the turbomachine (), intended for attaching the turbomachine () to an aircraft pylon ().

Turbomachine comprising a means of suspension

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

A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longitudinal axis.

Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine

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

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

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.

Growing community of inventors

Moissy-Cramayel, France

Quentin Matthias Emmanuel Garnaud