Bypass turbojet engine associated with a thrust reverser...

Details Bypass turbojet engine associated with a thrust reverser... Bypass turbojet engine associated with a thrust reverser...

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 1/56 (2006.01) F02K 1/52 (2006.01)

Patent

CA 2240094

In a bypass turbojet engine associated with a thrust reverser, the internal structure (11) forming the primary cowling of the turbojet and the external structure (12) supporting the said reverser (10) have no link in the lower portion of the structures (11, 12) and between them (11, 12) provide an annular passage (15) for conducting flow. A fairing element (25) is added in the said passage (15) on the downstream side of an arm (3) forming the supporting structure of the outer wall of the aft fan duct of the turbojet

Dans un turboréacteur à double flux associé à un inverseur de poussée, la structure interne (11) formant le capot primaire du turboréacteur et la structure externe (12) supportant ledit inverseur (10) ne comportent aucune liaison en partie inférieure des structures (11, 12) et ménagent entre elles (11, 12) un canal annulaire (15) de conduit de flux. Un carénage (25) est adjoint dans ledit canal (15) au côté aval d'un bras (3) formant la structure de support de la paroi externe du conduit arrière de soufflante du turboréacteur.

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