Aircelle Limited

Snecma

Safran Aircraft Engines

Safran Nacelles

Nicolas Dezeustre

Herve Hurlin

Olivier Kerbler

Bertrand Desjoyeaux

Wouter Balk

Patrick Gonidec

Pierre Caruel

Gilles Alain Charier

Patrick Boileau

Pierre Moradell-Casellas

François Gallet

Hervé Hurlin

Loic Le Boulicaut

Dylan Laurent Pascal Tassery

Arnaud Oudin

Patrick Stella

Ingrid Pitiot

Loïc Le Boulicaut

A method for repairing a turbomachine air intake lip including a damaged area whose shape differs from the initial shape of the lip, includes identifying the damage; depositing a filler material on the damaged area so as to give it a shape identical to the initial shape; inspecting the shape of the lip; and inspecting the performed repair.

Method for repairing an air intake lip

A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis.

Rear nacelle assembly for a turbojet engine

A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

Aircraft engine air flow straightening vane and associated flow straightening structure

A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means.

Thrust reverser device without a control rod in the stream

An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway.

Thrust reverser for an aircraft jet engine

A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means.

Nacelle for an aircraft bypass turbojet engine

An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.

Air intake structure for turbojet engine nacelle

A propulsion system has a nacelle, and inside this nacelle, a dual flow turbojet engine includes a fan case in which are located a fan and an assembly of fixed flow-rectifying vanes. This propulsion system includes a thrust inverter located between the fan and the assembly of the fixed flow-rectifying vanes. In particular, the thrust inverter includes a plurality of windows formed in the fan case and thrust inversion flaps to send back the secondary airflow toward the outside and toward the front of the nacelle, through the windows. The thrust inversion flaps pivotally move between a normal operating position in which they allow the passage of the secondary airflow and block the windows, and a thrust inversion position in which they block the passage and clear the windows.

Aircraft propulsion system provided with reverse thrust means

A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser.

Thrust reverser having locking/unlocking cascade vanes

A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Turbojet engine nacelle

An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing.

Assembly for attaching the hangers from which an aircraft propulsion unit is suspended

An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.

Growing community of inventors

Le Havre, France

Nicolas Dezeustre