RING CHAMBER OF LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: mechanical engineering; engines using for their operation cryogenic components, such as oxygen and hydrogen. SUBSTANCE: ring chamber of rocket engine has nozzle, combustion chamber with mixing head arranged inside nozzle and fuel and oxidizer supply manifold. Combustion chamber has profiled inner wall placed along longitudinal axis of chamber. Cooled cylinder is installed inside combustion chamber. One end of cylinder is connected with mixing head, and the other, with central part of nozzle, forming together with profiled inner wall of combustion chamber a ring critical section. Space of fuel supply manifold is divided into three parts isolated from each other. One part of space is connected with fuel supply space of mixing head, and two other parts, with spaces of cooling duct of ring combustion chamber and cylinder which are connected to each other. EFFECT: provision of high specific thrust pulse at minimum overall dimensions of chamber. 2 cl, 4 dwg