Aircelle Limited

Jerome Collier

Guy Bernard Vauchel

Nicolas Hillereau

Guillaume Lefort

Pierre-Alain Chouard

Jean-Philippe Joret

Francois Conte

Patrice Dhainault

Anne-Laure Gibouin

Jean-Francois Cribelier

Regis Fassier

The invention relates to a securing plate () for removably securing a one-piece propulsion unit () to a wing of an aircraft, characterised in that it includes first connection means () for securing the plate to the wing, second connection means () for securing the one-piece propulsion unit to the plate and third connection means () for securing a pair of longitudinal handling members () to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.

Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit

The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure () that defines, together with an inner concentric structure () for surrounding the downstream portion of the turbojet, an annular flow channel (), characterised in that a portion at least of said inner structure () is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.

Nacelle for the jet engine of an aircraft

The present invention relates, on the one hand, to a nacelle () for a double flow turboreactor () comprising a front air intake section (), a median section () intended for surrounding a fan () of the turboreactor and a rear section (), said rear section having an internal structure () intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon () intended to be connected to a fixed structure () of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.

Structural nacelle

A translatable thrust inverter with grids for a turbojet, that defines at least a portion of the downstream section of a nacelle housing the turbojet. The thrust reversal system includes a front frame secured to a fixed portion of the nacelle and bearing. A first side includes cylinders for the translational actuation of at least one mobile cowling. A second side includes grids for inverting the peripheral thrusts, wherein the front frame includes a fixed portion for securing the front frame to the fixed portion of the nacelle and bearing the diversion grids. The system further includes a portion mounted so as to be capable of translational movement along the longitudinal axis of the nacelle and on which one end of the cowling actuation cylinders is attached, wherein the fixed and mobile portions of the front frame can be removably connected to each other by locking means.

Translatable jet engine thrust reverser configuration providing improved maintenance access

The nacelle () comprises an air intake () upstream of the turbojet engine (), a middle section () an internal casing () of which is intended to surround a fan () of the turbojet engine (), and a downstream section () comprising an external structure (which is rigidly connected to a downstream part of the casing () of the fan () so as to support the turbojet engine () and has means of attachment to a strut () intended to be connected to a fixed structure () of an aeroplane.

Growing community of inventors

Le Havre, France

Jerome Collier