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

FIELD: engines and pumps.

SUBSTANCE: proposed engine chamber combustion chamber with regenerative cooling, throat and nozzle, mixing head including housing, unit to feed oxidiser, mainly, oxygen, primary fuel feed tank, extra fuel feed tank and fire bottom unit. Coaxial aligned-jet nozzles making central and peripheral zones are arranged in said units in concentric circles. Said coaxial aligned-jet nozzles include hollow nozzle communicating oxidiser zone with fire zone, sleeve covering said nozzle with clearance to communicate the primary fuel unit with fire zone. Note here that nozzles of at least central zone nozzles have radial grooves at their outlets composed of alternating ledges and recesses. Note here that said radial grooves are arranged to make perimeter of jet central part limited by beam generatrices not exceeding 3s while beam length equals 2.3-2.5 s where s is beam thickness. Note here that said beams are three in number. Note also that the sleeve between tip ledges has channels with outlets open to fire zone and inlets communicated with extra fuel unit chamber.

EFFECT: higher efficiency of combustion.

1 dwg