ADJUSTABLE SUPERSONIC NOZZLE OF GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02K1/80 F02K1/12 

FIELD: engines and pumps.

SUBSTANCE: adjustable supersonic nozzle of a gas turbine engine comprises a housing and subsonic and outer flaps hinged thereon and connected with supersonic flaps. Each external flap is designed as a hollow beam of variable stiffness with embedded brackets, the central and the terminal ones, fixed thereon. The terminal bracket is provided with a sliding bearing, doubled in the circumferential direction, which contacts with the guide groove of the box profile with the butt open at the nozzle outlet, which is formed integrally with the supersonic flap. The guide grooveof the box profile is made inclined to the supersonic flap sheet at an angle of 5…8 degrees with the apex directed to the nozzle housing.

EFFECT: invention allows to improve engine cooling, increase the operation reliability of the nozzle with minimal gaps between the outer and supersonic flaps at all engine operating modes, to reduce the load on the nacelle.

3 cl, 6 dwg