METHOD OF FUEL COMPONENTS FEED IN LIQUID PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2015 - IPC F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: fuel components are fed into rocket engine combustion chamber by nozzles from appropriate chambers of mixing head. The latter comprises outer, mid and fire bottoms that make the propellant and oxidiser feed units and, preferably, that for fire bottom cooling. Said bottoms are jointed by nozzles, studs, soldering and welding. Note here that propellant and oxidiser nozzles feature primarily a single-component design and are arranged at the head central zone staggered in fire bottom with further changeover to concentric configuration in the head peripheral zone. Studs are arranged in circle in the mixing head peripheral zone. Nozzles in fire bottom central zone make a square. Note here that nozzles located at square sides at mixing head central part and those located on two beams extending from square to periphery at every square side penetrate into chamber fire cavity behind the fire bottom to make anti-pulsation webs. Every peripheral nozzle extending relative to fire bottom is connected with propellant unit inside and located at intersections of studs circle with said beams of extending nozzles. Said beams make the extensions of square sides to connect its vertices with mixing head peripheral head. Every stud has at least three channels to communicate combustion chamber inside with that of propellant unit composed by mid and fire bottoms. Note here that outlet parts of said channels are located parallel with combustion chamber axis. Major part of said propellant and all oxidiser are fed via staggered nozzles. Propellant remainder is fed via propellant nozzles located arranged in the head peripheral zone and channels made in studs.

EFFECT: higher reliability and stability of mixing head operation, higher specific thrust pulse.

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