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. An adjustable nozzle of a turbojet engine contains a sequentially mounted housing having a rectangular shape in the output section, upper and lower subsonic flaps and upper and lower supersonic flaps pivotally connected to the corresponding subsonic flaps, as well as side walls rigidly connected to the housing, according to the present invention is equipped with heat shields and sealing elements. The housing is equipped with an outlet flange rigidly connected to the side walls at the ends, and each of the subsonic flaps is pivotally connected to the side walls. The heat shields are installed on the side of the flow part in the housing, as well as on the side walls and subsonic flaps and are rigidly fixed on the housing, side walls and subsonic flaps, respectively, with the formation of a cooling path between the heat shields and the mentioned structural elements, the entrance to which is communicated with the external circuit of the engine. Each of the sealing elements is installed between the upper end of the output flange and the nearby end of the upper subsonic flap, as well as between the lower end of the output flange and the nearby end of the lower subsonic flap and is rigidly connected to the output flange. In the gaps between the heat shields installed in the housing and on the subsonic flaps, sealing spacers are installed, each of which is rigidly connected to a nearby sealing element by means of guide elements located with a gap relative to each other and installed between the sealing elements and their corresponding sealing spacers in the cooling path.

EFFECT: reduction in losses is achieved when gas flows inside the flow part, including in the cooling path and the external flow around the adjustable nozzle by increasing the rigidity of its structural elements and reducing leaks from the flow part and the cooling path while maintaining its control parameters, which increases its efficiency and that of the turbojet engine as a whole.

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