ROCKET ENGINE NOZZLE Russian patent published in 2015 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engineering and can be used at creation of rocket engine nozzles, namely at development of a design of nozzles of liquid-propellant engines, which have a radiation-cooled nozzle extension. The rocket engine nozzle has a contour in the form of an axially doubled bell with a fracture of a contour line between two bell shapes. Fracture of the contour of the rocket engine nozzle is made in the form of an arc of a circle, the beginning and the end of which is determined with its contact points of contours of the first and the second bell shapes. Contour of the second bell shape is shaped as per a curve of the second order with an inclination angle to the symmetry axis of the rocket nozzle at the point of the fracture end of the rocket nozzle contour, which is larger than the inclination angle increased by 8° of the contour of the first bell shape to the symmetry axis of the rocket nozzle at the beginning point of the contour fracture.

EFFECT: invention allows decreasing evaluation temperature of the end part of the rocket engine nozzle at minimum reduction of effective specific thrust impulse.

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