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, a flap control system connected to the flaps by means of control mechanisms. The nozzle is equipped with six traverses mounted on the body, three at the top and bottom. The fastening of subsonic flaps is disclosed, as well as control mechanisms are disclosed, including six subsonic flap mechanisms and four supersonic flap mechanisms equally located in the upper and lower parts of the adjustable nozzle.

EFFECT: increase in the rigidity of the nozzle elements.

5 cl, 3 dwg