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. The adjustable nozzle of a turbojet engine includes a housing having a rectangular shape in the outlet section, side walls fixed on the housing, subsonic doors, supersonic doors hinged on subsonic doors, forming a flow part with controlled critical and outlet sections, a valve control system connected to subsonic doors and supersonic shutters through control mechanisms. Subsonic flaps are hinged on the side walls. The housing is made symmetrical with respect to the vertical longitudinal plane, the nozzle is equipped with six traverses fixed on the housing three in the upper and lower parts, two horizontal power beams. Control mechanisms are mounted on traverses and pivotally connected to the latter. The housing includes an inlet annular flange, a power belt and an outlet flange. The front plane of the inlet annular flange is rotated relative to the horizontal, perpendicular to the axis of the gas turbine engine, at an angle of up to 5° inclusive. The power belt is made outside the flow part in the form of two transverse walls fixed on the housing shell, and an outer shelf protruding beyond the dimensions of the transverse walls and containing flat horizontal platforms on the outer surface in its upper and lower parts. In addition, the power belt contains two boxes with lugs, while the lugs are located in such a way that there are two of them in each wall of the power belt, the lugs protrude inside the box, and the circumferential coordinate of the centers of the lugs deviates from the horizontal and is in the range from 20° to 35°. The outer shelf in the area of ​​the box has a cutout and protrudes relative to the walls more than in other places of the power belt. Horizontal power beams are fixed on the corresponding straight sections of the outlet flange, moreover, each crosshead is fixed with the front part on the corresponding flat horizontal platform, and with the rear part on the corresponding horizontal power beam. The shell in the place of fixing the transverse walls is made with a thickening.

EFFECT: invention reduces losses during gas flow inside the flow path and external flow around the adjustable nozzle by increasing the rigidity of its structural elements and reducing overall dimensions while maintaining its control parameters, which increases its efficiency and the turbojet engine as a whole.

2 cl, 4 dwg