Nacelle for the jet engine of an aircraft

Details Nacelle for the jet engine of an aircraft Nacelle for the jet engine of an aircraft

B - Operations, Transporting

64

D

B64D 29/08 (2006.01)

Patent

CA 2677423

The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) 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.

La présente invention se rapporte à une nacelle pour turboréacteur, du type comportant une structure aval comprenant une structure externe (6) qui définit, avec une structure interne (9) concentrique destinée à entourer une partie aval du turboréacteur, un canal annulaire d'écoulement (8), caractérisée en ce qu'au moins une partie de ladite structure interne (9) est montée mobile en translation le long d'un axe longitudinal' de la nacelle de manière à pouvoir se déplacer entre une position de travail dans laquelle la structure interne fait office de carter de la partie aval du turboréacteur et une position de maintenance dans laquelle la structure interne découvre ladite partie aval du turboréacteur.

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