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

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field aviation engine-building, namely to design of the turbojet engines flat nozzles. Flat nozzle comprises successively mounted and hingedly connected to each other housing, subsonic doors and supersonic doors, as well as external flaps connected to the hull and supersonic flaps, as well as fairings, each of which is made in a U-shaped cross-section and contacts the corresponding supersonic flap along the lateral surfaces. On the side of the cut of the flat nozzle, the fairing is in contact with the outer surface of the supersonic leaf, and from the opposite side of the fairing a cylindrical tip is made, contacting the outer surface with the response surface of the adjacent end of the corresponding outer leaf. Longitudinal axis of the cylindrical end is aligned with the axis of rotation of the corresponding supersonic leaf. Every fairing is rigidly fixed on the corresponding supersonic leaf in places of contact with the latter. Every flap is connected to the hull by means of at least one bracket, one end rigidly connected to the first and the other end pivotally connected to the latter. With the corresponding supersonic flap, any of the outer flaps is connected by means of at least one bracket rigidly connected to the latter, and at least one link connected to the first by means of a hinged connection. Axis of rotation of said articulated joint is aligned with the axis of rotation of the supersonic flap. Bracket with the linkage is articulated.

EFFECT: invention makes it possible to reduce the loss of thrust of a flat nozzle by reducing the bottom resistance.

1 cl, 4 dwg