FIELD: engines and pumps.
SUBSTANCE: invention relates to bypass turbojet engine nacelle (10), forming fan casing, containing first fairing element (12), upstream and second fairing element (13), forming the nozzle; wherein second element is movable in translational displacement between position, whereat it ensures aerodynamic integrity of nacelle, and downstream position opening flow reversal hole; wherein thrust reversing device is arranged in nacelle and comprises flow flaps-reversers (17), as well as grids (15) for radial flow direction. Nacelle is characterized by that grids (15) for radial flow direction are movable in translational displacement along nacelle axis between position, in which they are retracted into fairing first element (12), and flow direction active position; wherein fan fairing second element (13) is rigidly connected with said direction grids (15); wherein flap-reversers (17) are installed movable in rotation around axes perpendicular to nacelle axis, and rigidly connected with grids (15).
EFFECT: invention provides use of ultra-short type nacelle, as well as location of nozzle control mechanism associated with thrust reversing mechanism location.
9 cl, 10 dwg
