Device for controlling propulsive flow mixture for aircraft...

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

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F02K 1/00 (2006.01) F01D 5/14 (2006.01) F02K 1/28 (2006.01)

Patent

CA 2460742

The invention concerns a device for controlling propulsive flow mixture (8, 9) at the output of an aircraft reactor, said propulsive flows (8, 9) consisting of a primary hot flow (8) exiting from an exhaust nozzle (1) of said reactor, and a secondary flow (9) flowing between the outer wall (2a) of said nozzle (1) and the inner wall of said reactor. The invention is characterized in that the wall (2) of said nozzle (1) includes a divergent trailing edge (3) so as to generate conditions for separating said primary flow (8) close to a threshold existence value and it comprises means for controlling (4) said primary flow (8), said control means (4) enabling to control the passage of said primary flow (8) from a separated state to a flow readhesion state, and vice-versa.

La présente invention se rapporte à un dispositif de contrôle de mélange de jets propulsifs (8, 9) à la sortie d'un réacteur d'avion, lesdits jets propulsifs (8, 9) étant composés d'un jet primaire chaud (8) sortant d'une tuyère (1) dudit réacteur, et d'un flux secondaire (9) s'écoulant entre la paroi externe (2a) de ladite tuyère (1) et la paroi interne dudit réacteur, caractérisé en ce que la paroi (2) de ladite tuyère (1) présente un bord de fuite (3) divergent de manière à générer les conditions d'un décollement dudit jet primaire (8) proche d'une valeur limite d'existence et en ce qu'il comporte des moyens de pilotage (4) dudit jet primaire (8), lesdits moyens de pilotage (4) permettant de contrôler le passage dudit jet primaire (8) d'un état décollé à un état recollé, et inversement.

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