LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2013 - IPC F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: nozzle tubular case flow section decrease from pylons to outlet, mainly, in the form of one confuser. Sleeve is arranged at tubular case outlet to make annular chamber between case outer surface and sleeve inner surface communicated with kerosene feed unit chamber. Helical channels are made in said annular chamber. Adjusting element, a chamfer made to vary its geometry in adjustment, is arranged at tubular case axial inlet. Said tubular case represents a split design. Blind tube outer surface arranged at tubular case outlet is provided with pylons to interact by their outer surfaces with case inner surface. Lengthwise axes of said pylons are located at definite angle to injector lengthwise axis. Pylon has channels with their inlets communicated with blind tube chamber while their outlets communicate with annular chamber formed by tubular case and blind tube. Axes of said pylons in said pylons oppose direction of helical channels axes in annular chamber between sleeve and tubular case outer surface. Said blind split tube consists of pylon part and adapter with jet arranged there between.

EFFECT: higher rocket engine efficiency.

4 cl, 5 dwg