FIELD: engine building.
SUBSTANCE: invention relates to double-circuit turbojet engines. An engine nacelle for a turbojet engine contains a thrust reverser system having at least one movable hood (8) made with the possibility of being diverted to a rear position of reverse thrust, inclined rotary leaves (10) at least partially closing annular flow channel (18), and opening side holes of this annular flow channel, equipped with lattices of the thrust reverser. At the same time, each movable hood (8) contains controlling segment (12) sliding in a transverse plane, return device (20) connecting immobile nacelle section (2) to this controlling segment (12) for its sliding to a reverser position, when diverting movable hood (8), and connecting leaf thrusts (16) connecting specified controlling segment (12) to rotary leaves (10), inclining specified leaves (10), providing closing of annular flow channel (18), when controlling segment (12) slides towards its reverser position.
EFFECT: invention provides reduction in aerodynamic losses in an annular flow channel, as well as an increase in performance of a reverser in a forward thrust position.
10 cl, 22 dwg
