TURBOJET ENGINE AXIS SYMMETRICAL TURNING NOZZLE Russian patent published in 2019 - IPC F02K1/78 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to the aviation equipment turbojet engines, in particular to the jet nozzles design. Turbojet engine rotary axisymmetric nozzle contains the stationary body with a spherical tip thereon, and movable relative to it rotary device, as well as the hydraulic changeover system. Rotary device is placed with possibility of the rotation about the axis installed across the engine longitudinal axis. Hydraulic changeover system is made in the form of two bushings, one is hinged on the fixed body, and the other is on the rotary device, hydraulically interconnected by the set into them and telescopically interconnected hollow angle pieces. One bushing cavity is connected to the engine hydraulic system, and cavity of the other is connected to the rotary device hydraulic system. Each of the angle pieces is provided with the tooth, inserted into the mating bushing groove. Each of the angle pieces is provided with the additional groove, into which a corresponding additional tooth is inserted, made on the mating bushing from the opposite side of the groove present thereon. Each bushing tooth and groove lie in the parallel planes.

EFFECT: invention allows to increase the rotating jet nozzle hydraulic changeover system reliability.

1 cl, 3 dwg