ADJUSTABLE SUPERSONIC NOZZLE OF TURBOJET ENGINE Russian patent published in 2018 - IPC F02K1/12 

FIELD: motors and pumps.

SUBSTANCE: controlled supersonic nozzle of a turbojet engine belongs to the field of aircraft engine construction. Nozzle contains a body, subsonic and external doors, that are attached to it with a hinge, supersonic doors, that are hinged to the subsonic doors and movably connected to the outer doors, drive of the doors and mechanism of synchronization of the subsonic and external doors, executed in the form of the main and additional levers, that are connected with a hinge to the subsonic and external doors, telescopic rods and pneumatic cylinders, installed on the external doors in the circumferential direction. Each telescopic rod is pivotally connected to the subsonic door with its one end, and the other end is connected to the external door and has stops to limit the change in the diameter of the outlet section of the nozzle relative to its critical section, wherein the hinges are located in the center of the longitudinal axes of the doors.

EFFECT: invention makes it possible to eliminate the transfer of load from the external doors and pneumatic cylinders when the telescopic links are closed and extended towards the body and the main lever, which reduces the elastic deformation of the rods and wear of their bearings, and thus improve the synchronization of the motion of external and supersonic doors, reduce the distortion of the shape of the nozzle's cut and, accordingly, increase the reliability of the engine.

1 cl, 7 dwg