ADJUSTABLE TURBOJET NOZZLE Russian patent published in 2022 - IPC F02K1/12 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, namely to the design of adjustable nozzles of turbojet engines. The adjustable nozzle of a turbojet engine contains a housing installed in series, having a rectangular shape in the outlet section. Each of the subsonic and supersonic flaps is made in a cross section of an angular shape formed by two plates connected at the ends at an obtuse angle, the apex of which is directed from the longitudinal axis of the turbojet engine. Each of the subsonic flaps is pivotally connected to the side walls. Between the upper end of the outlet flange and the adjacent end of the upper subsonic flap, as well as between the lower end of the outlet flange and the adjacent end of the lower subsonic flap, a sealing element is installed, rigidly connected to the outlet flange. The surfaces of the sealing elements adjacent to the respective subsonic flaps are made with the possibility of contact with the latter and are formed by two conical surfaces, the axes of the cones of which coincide with the axis of rotation of the corresponding subsonic flap. Each of the adjacent surfaces of the subsonic and supersonic flaps, located along the axes of their hinged joints, is made conical.

EFFECT: increasing the rigidity of the nozzle elements.

1 cl, 2 dwg