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. Adjustable nozzle of a turbojet engine is equipped with mechanisms for increasing the rigidity of the side walls, two vertical power beams, each subsonic flap is hingedly connected with the side walls. The body includes an output flange, rigidly fixed on the end surface whereof are the side walls, wherein the power beams are secured on the vertical sections of the output flange. Mechanisms for increasing the transverse rigidity, connected with the latter and with the body so as to be able to move along the flow part, are hingedly secured on the power beams. Each of the side walls is equipped with flat heat-protective shields and tips, symmetrical relative to the horizontal plane, constitutes a thin-walled shaped panel consisting of a front, middle and back parts secured together, and made tapering in the width thereof from the point of contact with the body, and the front part is equipped with a flange in the area of the front end in contact with the body. The profile of each panel comprises protrusions made in the form of cylindrical sleeves, the axis whereof is perpendicular to the plane of the screens, for securing the latter, the ends and for installing the hinged connections with subsonic flaps, as well as external stiffening ribs, means of connection with the mechanisms for increasing the rigidity of the side walls, three longitudinal convexities and six transverse convexities located between the longitudinal ones, wherein all the convexities are directed outward relative to the flow part. The longitudinal convexities are made from the flange, the central one thereof is made wider than the extreme ones, narrowed and reinforced with two external stiffening ribs by the flange, with a concavity along the outer surface at the point of maximum distance from the flow part, and passes through three parts of the panel. The extreme longitudinal convexities are made on the front and middle parts, two wide transverse convexities are made on the front part, four narrow transverse convexities are made on the middle part, wherein two means of connection with a mechanism for increasing the rigidity of the side walls are made on two of said convexities at a maximum distance from the flange, wherein each of said means is stiffened with an external stiffening rib at the point of connection with the back part. Acutout with holes on the edge is made at the outlet in the back part, wherein a tip is installed, following the shape thereof, the protrusions for installing the ends are located periodically along the edges of the cutout, each of the protrusions comprises a pair of eyelets and is stiffened with a stiffening rib at the central longitudinal bulge or at the point of connection with the middle part, wherein the panel is made with a greater thickness along the points of connection of the parts. Protrusions for installing the hinged connections with subsonic flaps are made between the edge of the panel and the extreme longitudinal convexities near the flange, wherein each of said protrusions is stiffened by three external stiffening ribs with the last one and one external stiffening rib with an extreme longitudinal convexity, the protrusions for mounting the screens are arranged in rows across the panel, and the protrusions for securing the ends are configured for mounting the screens.

EFFECT: invention allows for an increase in the performance coefficient of the nozzle and the gas turbine engine as a whole.

3 cl, 3 dwg