Aircelle Limited

Hurel Hispano

Xavier Raymond Yves Lore

Pascal-Marie Paul Marcel Soulier

Thierry Jacques Albert Le Docte

Hazem Kioua

Michel Philippe Dehu

Aurélie De Sorbay

Xavier Holay

Michel Christian Marie Jean

Olivier Conet

The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Assembly centering device for turbojet engine nacelle

The invention relates to a locking device () that includes at least one locking system (), intended to be placed on a first moving element (), and a retaining member (), intended to be placed on a second moving element (), the locking system () having a first hook () designed to engage with the retaining member so as to lock the locking device (). The locking system () includes at least a second hook () set back from the first hook () so as to engage with the retaining member in the event of the first hook () breaking.

Locking device

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

The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser () comprising guide means () for the movable parts (), and the guide means () comprising rails () attached to the movable parts () and tracks () attached to the longitudinal members (). According to the invention, the locking system () comprises locks () located at the end () of each track () in the opening direction (), each lock comprising a bolt () capable of preventing the rail () moving in the opening direction ().

Growing community of inventors

Beuzeville la Grenier, France

Xavier Raymond Yves Lore