Nacelle for the jet engine of an aircraft

摘要

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.

主权项

1. A nacelle for a turbojet engine, of the type comprising a downstream structure comprising:
an outer structure which defines, with a concentric inner structure surrounding a downstream part of the turbojet engine, an annular flow duct, wherein at least part of said inner structure is slidably mounted such that the inner structure moves translationally along a longitudinal axis of the nacelle, without pivoting, so that the inner structure can be moved between a working position in which the inner structure acts as a case for the downstream part of the turbojet engine and a maintenance position in which the inner structure uncovers said downstream part of the turbojet engine, wherein the inner structure moves translationally with respect to the nacelle by means of at least one pair of rails and slides, each rail cooperating with one slide having a curved portion.