TURBOJET ENGINE FLAT NOZZLE Russian patent published in 2018 - IPC F02K1/06 F02K1/12 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field aviation engine-building, namely to design of the turbojet engines flat nozzles. Turbojet engine flat nozzle contains body with sidewalls fixed thereto, subsonic, supersonic and external flaps, as well as longitudinal levers, subsonic flaps control levers, subsonic flaps hydraulic control cylinders and brackets. Subsonic flaps are pivotally secured to the side walls and pivotally connected to the supersonic flaps. By one end the outer flaps are pivotally connected to the side walls, and by the other one are installed in the guides made in supersonic flaps. Brackets are mounted on the body and are connected to the longitudinal levers by means of tie-rods. Brackets are provided with eyelets, to which the hydraulic cylinders bodies are pivotally attached, connected by rods to the subsonic flaps control levers. By one end the longitudinal levers are installed from the outside of the body near the nozzle horizontal symmetry plane, and by the other end are connected to the side walls near the nozzle critical cross-section.

EFFECT: invention allows to increase the flat nozzle strength due to the side walls deformation reducing, to reduce the body and the flat nozzle weight, and to provide the subsonic and supersonic flaps hermetic articulation with the nozzle side walls.

1 cl, 7 dwg