Bypass turbojet engine nacelle

Details Bypass turbojet engine nacelle Bypass turbojet engine nacelle

B - Operations, Transporting

64

D

B64D 27/18 (2006.01)

Patent

CA 2665425

The nacelle (1) comprises an air intake (5) upstream of the turbojet engine (2), a middle section (6) an internal casing (6a) of which is intended to surround a fan (3) of the turbojet engine (2), and a downstream section (7) comprising an external structure (7a) which is rigidly connected to a downstream part of the casing (6a) of the fan (3) so as to support the turbojet engine (2) and has means of attachment to a strut (12) intended to be connected to a fixed structure (13) of an aeroplane.

La nacelle (1) comprend une entrée d'air (5) en amont du turboréacteur (2), une section médiane (6) dont un carter interne (6a) est destiné à entourer une soufflante (3) du turboréacteur (2), et une section aval (7) comportant une structure externe (7a), laquelle est reliée rigidement à une partie aval du carter (6a) de soufflante (3) de manière à soutenir le turboréacteur (2) et possède des moyens d'accrochage à un pylône (12) destiné à être lié à une structure fixe (13) d'un avion.

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