LIQUID PROPELLANT ROCKET ENGINE ANNULAR CHAMBER Russian patent published in 2010 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: proposed chamber comprises nozzle, cooled combustion chamber with mixing head arranged axially symmetric inside the nozzle and fuel and oxidiser feed branch pipes. Said combustion chamber features profiled inner wall and is arranged along its lengthwise axis. It houses cooled cylinder with one face jointed with mixing head and another face connected with the nozzle central part, to form, together with the chamber profiled inner wall, an annular critical section. Cooled cylinder outer surface and combustion chamber inner surface are furnished with lengthwise ribs.

EFFECT: improved heat exchange between combustion products and coolant.

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