Turbojet thrust reverser having doors with inverted flux...

F - Mech Eng,Light,Heat,Weapons – 02 – K

Patent

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60/98

F02K 1/70 (2006.01)

Patent

CA 2002466

A pivoting door (107) of a thrust reverser of the bypass flow of a bypass jet engine comprises an outer panel (9) whose outer surface conforms to the nacelle outer profile (4) and fixed aft portion (3) of the reverser and an inner panel (111) whose inner surface (111a) blends, in forward thrust, with the theoretical outer surface of the bypass airstream. Between the said inner panels (111) and outer panels (9) is a passage (20) with an opening (21, 22) at each end, on the inner side of the door and forming, when operating in reverse thrust, a miniature exhaust nozzle through which flows a portion (15b) of the reversed thrust (15a), of which it ensures optimal deflection.

Une porte basculante (107) d'un inverseur de poussée du flux secondaire d'un turboréacteur à double flux comporte un panneau externe (9) dont la surface externe se raccorde au profil externe de nacelle (4) et de partie arrière fixe (3) d'inverseur et un panneau interne (111) dont la surface interne (llla) se confond, en poussée directe, avec la surface théorique de délimitation de la veine du flux secondaire. Entre lesdits panneaux interne (111) et externe (9) est ménagé un passage (20) présentant une ouverture (21, 22) à chaque extrémité, du côté interne de la porte et formant, lors du fonctionnement en inversion de poussée, une mini-tuyère d'écoulement où passe une partie (15b) du flux inversé (15a) dont elle assure la déviation optimale.

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