Aircelle Limited

Safran Nacelles

Xavier Cazuc

Jean-Philippe Joret

Sébastien Laurent Marie Pascal

Guy Bernard Vauchel

Vincent Jean-François Peyron

Pierre Caruel

Patrick André Boileau

Xavier Bouteiller

John Moutier

Fabien Jourdan

Christophe Thorel

Laurent Albert Blin

Vincent Dutot

Stephane Riquier

Eric Thisse

Laure Hamel

Meril Dehez

Jean-Phillipe Joret

A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.

Device for attaching a connecting rod small end for a thrust reversal cascade flap

The invention relates to an assembly () which comprises a front frame () of a thrust reverser structure of an aircraft nacelle and at least one cascade (). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading () upstream of the cascade from a covering area () between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.

Front frame and deflection grid of a thrust reverser of an aircraft nacelle

A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.

Thrust reverser for an aircraft bypass turbojet engine nacelle

A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Thrust reverser with anti-buckling actuating system

An acoustic treatment device for an aircraft turbojet engine nacelle forms an annular ring including several sections, each section having a sound absorption structure, an outer skin and two lateral skins attached to the inner air inlet shroud of such a nacelle by fasteners, and the sections being connected to each other by battens.

Acoustic treatment device for an aircraft turbojet engine nacelle

The present disclosure relates to a front frame for an aircraft nacelle comprising a turbojet mounted on a suspension strut, said nacelle comprising a thrust reverser including an actuator designed to open a thrust reversal cowling. The front frame comprises a tubular torsion box, a first straight attachment edge intended to attach the box to a turbojet casing and a second straight attachment edge intended to attach the box to air flow diversion means. The front frame is arranged to transmit tensile and compressive loads between the turbojet casing and the air flow diversion means and torsion loads absorbed by the suspension strut. The front frame is characterized in that the tubular torsion box has a semi-elliptical or elliptical cross-section.

Front frame for a cascade thrust reverser structure

A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

Flattened nacelle of a turbojet engine

A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure.

Cellular acoustic structure for a turbojet engine and turbojet engine incorporating at least one such structure

The invention relates to a nacelle including an air intake upstream from the jet engine (), a medium section surrounding the fan of the jet engine (), and a downstream section. The nacelle further includes at least one pair of mobile cowlings () provided on both sides of a vertical longitudinal symmetry plane of the nacelle and hinged essentially parallel to a longitudinal axis (A) of the nacelle so they can be opened to provide access to the jet engine (). The mobile cowlings () are paired by fastening means () so that they can be hinged on each other about separate or overlapping axes (). Each mobile cowling () comprises permanent connection means or means () for connecting it temporarily by rotation and in closed position to a fixed structure () of the nacelle.

Side-opening jet engine nacelle

The invention relates to a device comprising gratings, which are used to form a reverse flow from a jet engine thrust flow. The inventive device comprises a plurality of flow diverter gratings which are disposed side-by-side at the outer edge of an annular thrust flow circulation channel. Each of the gratings comprises a plurality of intersecting inner transverse blades and inner longitudinal blades, two adjacent gratings being separated by a side clearance which generates a leakage flow. The device also comprises means of re-directing the aforementioned leakage flow in a direction such as to increase the effectiveness of the reverse flow, said re-direction means comprising aerodynamic appendages which are mounted to at least one outer longitudinal edge of each grating.

Growing community of inventors

Le Havre Rouelles, France

Xavier Cazuc