Aircelle Limited

Safran Nacelles

Pascal-Marie Paul Marcel Soulier

Aurélie De Sorbay

Thierry Jacques Albert Le Docte

Xavier Raymond Yves Lore

Jean-Pierre Guegou

Jean-Bernard Guillon

A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.

Gas ejection cone for aircraft turbojet engines

An actuating device is provided for a locking system which locks one of half-shells of a jet engine nacelle with respect to the other half-shell. The actuating device includes a fixed body in which an actuating rod is translationally and rotationally mounted with respect to the rod's longitudinal axis, and the fixed body has a track cooperating with a follower projecting from the actuating rod. In particular, the actuating rod includes a first end equipped with a handle and a second end connected to the locking system. The track has a middle part running parallel to the longitudinal axis, a first end part and a second end part formed on each side of the middle part, each of the end parts running perpendicular to the longitudinal axis.

Actuating device for a locking system of an engine nacelle

The invention relates to a coupling device () intended to connect first and second elements () which can move relative to one another, comprising a connecting rod () coupled to the first and second movable elements () at first and second ends () respectively, at least one of the ends of the connecting rod () having a head () intended to cooperate with locking means () belonging to the corresponding movable element () so as to removably fasten the connecting rod () to the corresponding movable element (), characterized in that the coupling device () comprises at least one telescopic guide member () serving to support and guide the connecting rod () during the movement of the movable elements (), having first and second ends () intended to be attached to first and second support elements () respectively.

Coupling device intended to connect first and second elements which can move relative to one another

The invention relates to a locking device () designed to be arranged in a junction region of a nacelle, comprising a locking system (), intended to be mounted on a first half-shell of the nacelle, engaging with a retention member () intended to be mounted on a second half-shell, the locking system () being actuable between a locked state and an unlocked state with respect to the retention number (), the locking system () and the retention member () being movable with respect to one another between a drawn-together position in which they can be locked with respect to one another and a spaced-apart position. The locking system () and/or the retention member () comprise locking means () designed to allow the locking system () to be locked with respect to the retention member () when they are in the drawn-together position and to prevent them from being locked when they are in the spaced-apart position.

Locking device designed to be arranged in a junction region of a nacelle

The present invention relates to a jet engine nacelle (), of the type comprising an aft section forming an external structure () which, together with a concentric internal structure () comprising an internal panel () intended to surround a down-stream portion of the jet engine, defines an annular flow duct for a so-called secondary stream (), characterized in that exhaust means () are formed in the internal panel such that any unwanted excess pressure is discharged into the annular duct.

Nacelle equipped with at least one excess pressure flap

The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure () comprising an inner panel () for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterized in that the exhaust means () are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Nacelle comprising at least one surge trap

Disclosed is a coupling device () intended to connect first and second elements which are articulated with respect to one another, wherein the device includes a compression element () designed to allow a compressive force to pass from one element to another in a first state, and a tension element () designed to allow a tensile force to pass from one element to another in a second state, the compression element additionally forming a substitution tension element designed to allow a tensile force to pass from one element to another in a third state corresponding to the fracturing of the tension element.

Growing community of inventors

Le Havre, France

Pascal-Marie Paul Marcel Soulier