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

FIELD: aircraft engineering.

SUBSTANCE: invention relates to the field of aircraft engine construction, namely to the design of adjustable nozzles of turbojet engines. The adjustable nozzle of a turbojet engine contains a body, subsonic and supersonic flaps pivotally connected to each other, side walls rigidly connected to the body, as well as elements of the external bypass and a flap control system. One transverse front and one transverse rear beams are installed on each supersonic leaf. At least three holes are made in each transverse front beam, two of which contain elements of control mechanisms with a gap. Each of the subsonic and supersonic flaps is made in a cross section in the form of an obtuse angle, the vertex of which is directed from the flow part of the engine. Each of the subsonic flaps is pivotally connected to the side flaps. The design of supersonic flaps and stiffeners on them, as well as the connection of the flaps with control mechanisms, is disclosed.

EFFECT: increase in the rigidity of the nozzle elements.

7 cl, 2 dwg