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

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, and in particular to the design of variable nozzles for turbojet engines. The specified effect is achieved in that the known adjustable nozzle of a turbojet engine, according to the present invention, comprises a housing with a rectangular outlet flange rigidly connected to the side walls at the ends and equipped with two vertical load-bearing beams mounted on its outer side surfaces, in this case, the movable flaps are made in the form of subsonic and supersonic flaps hinged to each other, and each subsonic flap is hingedly connected to the side walls, in addition, the mechanism for reducing the bending deformation of the fixed side walls is made in the form of at least two brackets mounted on the body, and at least two horizontal beams, each of which is pivotally attached with its central part to the corresponding vertical load-bearing beam, while the opposite ends of each of the horizontal beams are connected to the body by means of a bracket, as well as to the corresponding side wall, with the possibility of displacement of the former relative to the latter along the longitudinal axis of the nozzle.

EFFECT: reduction of losses during gas flow inside the flow path and external flow around an adjustable nozzle by increasing the rigidity of its structural elements while maintaining its control parameters, which increases its efficiency and the gas turbine engine as a whole.

3 cl, 1 dwg