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 sequentially mounted body, subsonic and supersonic flaps pivotally connected to each other, side walls rigidly connected to the body, as well as flap control mechanisms. The nozzle is equipped with two vertical power beams with holes and two horizontal power beams containing eyelets, as well as six traverses fixed to the body. Each subsonic flap is pivotally connected to the side walls. The housing is provided with an outlet flange rigidly connected to the side walls at the ends, while grooves with holes in their walls are made from the outside along each rectilinear section of the outlet flange. The placement of eyelets, vertical power beams and traverse are disclosed, as well as the design of horizontal power beams is disclosed.

EFFECT: reducing losses during the flow of gas inside the flow part and the external flow around the adjustable nozzle by increasing the rigidity of its structural elements and reducing overall dimensions while maintaining the parameters of its regulation.

1 cl, 2 dwg