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

FIELD: engine building.

SUBSTANCE: invention relates to the field of aviation engine building. The adjustable nozzle of a turbojet engine is equipped with six traverses secured on the body in threes in the upper and lower parts thereof, and four connecting apparatuses, each secured on the body between the traverses. Each subsonic flap is hingedly connected with the side walls, the power elements of the flap control system are secured on the body and connected with the subsonic flaps and the supersonic flaps by means of control mechanisms. The flap control system includes four hydraulic cylinders, one for each supersonic flap control mechanism, secured on the body by means of connecting apparatuses, four hydraulic cylinders and two pneumatic cylinders, each connected with one subsonic flap control mechanism and secured on the body by means of traverses, a communication system, and control units. Each connecting apparatus includes a bracket secured on the body, a lever secured hingedly on the bracket, and two rods connecting the lever by hinges with the adjacent traverses. Each hydraulic cylinder or pneumatic cylinder of the subsonic flap mechanisms is secured on the corresponding traverse by means of a hinge, and each hydraulic cylinder of the supersonic flap mechanisms is secured on the corresponding lever by means of a hinge. The eyelet for securing the hydraulic cylinder on the lever is located between the eyelets for securing the rods and the eyelets for securing the lever to the bracket. Each hydraulic cylinder and pneumatic cylinder have a feedback sensor, and each control mechanism is connected with the corresponding hydraulic cylinder or pneumatic cylinder by means of a hinge. The pneumatic cylinders are connected with the central subsonic flap mechanisms in the upper and lower parts of the adjustable nozzle.

EFFECT: invention allows for an increase in the performance coefficient of the engine.

2 cl, 2 dwg