AIRCRAFT TURBOJET ENGINE FLAT NOZZLE Russian patent published in 2018 - IPC F02K1/12 F02K1/82 

FIELD: motors and pumps.

SUBSTANCE: invention relates to the field aviation engine-building, in particular, to the turbojet engines flat nozzles design. Flat nozzle comprises body, subsonic flaps hinged to the body, supersonic flaps pivotally connected to the subsonic ones, and external flaps, by one end hinged to the body, and by the other are connected to supersonic flaps. On the supersonic flaps outer surface across the aircraft turbojet engine longitudinal axis power elements are installed. Each power element is connected to the supersonic flap by means of located along it odd number of fasteners. Each of the fastening joints is made in the form of two connecting elements with lugs, rigidly connected to the power element and the supersonic flap, respectively, and the fixing element. One of the lugs in each of the fasteners, except for the fastening joint located closest to the corresponding supersonic flap longitudinal axis of symmetry, is made stretched across the aircraft turbojet engine longitudinal axis, with possibility of the fixing element displacement along it.

EFFECT: invention allows to increase the flat nozzle strength due to the supersonic flaps deformation reduction, provide the subsonic and supersonic flaps hermetic articulation with the nozzle side walls, and also reduce the flat nozzle weight in general.

3 cl, 5 dwg