F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
F02K 1/46 (2006.01) F02K 1/38 (2006.01)
Patent
CA 2652363
This nacelle (201) for an aircraft turbojet includes an internal downstream structure (13) and an external downstream structure (15) delimiting an interior flow channel (14) for a secondary flow generated by the turbojet, the external downstream channel comprising at least one distribution line (18, 19a, 19b, 20) terminating at the outlet of the turbojet and being intended to be connected to a sound-reducing fluid supply source arranged upstream from the external downstream structure. This external downstream structure (15) is equipped with a thrust reversal device. The distribution line includes at least one supply line (19a, 19b) capable of ensuring the passage of said fluid from said supply source towards the outlet of the turbojet at least when said reversal device is in its off position.
Cette nacelle (201) pour turboréacteur d'un aéronef comprend une structure interne aval (13) et une structure externe aval (15) délimitant un canal intérieur (14) d'écoulement d'un flux secondaire engendré par le turboréacteur, la structure externe aval comportant au moins un circuit de distribution (18, 19a, 19b, 20) débouchant en sortie du turboréacteur et étant destiné à être raccordé à une source d'alimentation en fluide de réduction sonore disposée en amont de la structure externe aval. Cette structure externe aval (15) est équipée d'un dispositif d'inversion de poussée. Le circuit de distribution comprend au moins un conduit d'alimentation (19a, 19b) apte à assurer le passage dudit fluide de ladite source d'alimentation vers la sortie du turboréacteur au moins lorsque ledit dispositif d'inversion est dans sa position de fermeture.
Portal Jean-Fabrice Marcel
Vauchel Guy Bernard
Aircelle
Ogilvy Renault Llp/s.e.n.c.r.l.,s.r.l.
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