Nacelle rear assembly for turbojet engine

Details Nacelle rear assembly for turbojet engine Nacelle rear assembly for turbojet engine

B - Operations, Transporting

64

D

B64D 33/04 (2006.01) B64D 29/00 (2006.01)

Patent

CA 2687454

The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding between an operational position in which it covers the gas generator (3) of said turbojet engine and defines an annular cold-air jet with said hood, and a maintenance position downstream from said operational position. The downstream portion (15) is conformed so as to be capable of sliding without blocking relative to said gas generator (3), and the inner structure includes an upstream portion (13) that can be separated from the downstream portion (15) and that includes at least two doors (13a, 13b) capable of opening towards the outside.

Cet ensemble arrière de nacelle pour turboréacteur, comprend : un capot, une structure interne en forme de fuseau dont au moins la partie arrière (15) est du type O-duct et est mobile par coulissèrent axial entre une position de fonctionnement dans laquelle elle recouvre le générateur de gaz (3) dudit turboréacteur et définit une veine annulaire d'air froid avec ledit capot, et une position de maintenance située en aval de ladite position de fonctionnement. Ladite partie aval (15) est conformée pour pouvoir coulisser sans blocage par rapport audit générateur de gaz (3), et cette structure interne comprend une partie amont (13) séparable de ladite partie aval (15) et comportant au moins deux portes (13a, 13b) aptes à s'ouvrir vers l'extérieur.

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