ADJUSTABLE SUPERSONIC NOZZLE OF TURBOJET ENGINE Russian patent published in 2016 - IPC F02K1/12 F02K1/78 

FIELD: engines.

SUBSTANCE: adjustable supersonic nozzle of turbojet engine relates to aviation engine-building. Adjustable supersonic nozzle comprises a body pivotally attached to it subsonic and outer flaps connected with supersonic flaps. Outer flaps are fitted with pneumatic cylinders with connected to them air feeds. Every air feed is designed as a central tube located along the longitudinal axis of the outer flap and is provided with an air changeover element attached to the nozzle body. Every air feed is equipped with a tee attached to the inner surface of the outer flap, a cavity of which communicates with the central and two additional tubes connected to rod ends of the adjacent air cylinders. Tubes have curved sections.

EFFECT: invention reduces thermal stresses arising in air feed elements and its connections with adjacent assemblies during engine operation, and also reduces the weight of the nozzle.

1 cl, 4 dwg