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

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering. Adjustable nozzle of a turbojet engine includes a housing having a rectangular shape in the outlet section, side walls fixed on the housing, subsonic flaps, supersonic flaps hinged to subsonic ones, forming a flow part with controlled critical and outlet sections, flaps control system. Nozzle is equipped with six traverses fixed on the housing by three in its upper and lower parts, and four connecting devices, each of which is installed on the housing between the traverses. Each subsonic flap is hinged to side walls, wherein control mechanisms include six mechanisms of subsonic flaps and four mechanisms of supersonic flaps equally located in upper and lower parts of adjustable nozzle. Flap control system includes load-bearing elements fixed on the body and connected to subsonic flaps and supersonic flaps by means of control mechanisms. Power elements are hydraulic cylinders with feedback sensor, one for each control mechanism, connected by means of hinges, communication system and control units providing independent control of subsonic and supersonic flaps in upper and lower parts of adjustable nozzle. Each connecting device includes a bracket fixed on the body, a lever pivotally fixed on the bracket, and two tie-rods pivotally connecting the lever with adjacent traverses. Each subsonic flap mechanisms hydraulic cylinder is fixed on the corresponding traverse by means of a hinge, and each hydraulic cylinder of supersonic flaps mechanisms is fixed on the corresponding lever by means of a hinge, besides, the eye for attachment of the hydraulic cylinder on the lever is located between the lugs of fastening of the rods and lugs of the lever attachment to the bracket.

EFFECT: invention provides higher efficiency of gas turbine engine.

1 cl, 2 dwg