THREE-COMPONENT LIQUID-PROPELLANT ROCKET ENGINE AND METHOD OF ITS OPERATION Russian patent published in 2010 - IPC F02K9/48 

Abstract RU 2386844 C1

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises at least one combustion chamber with jet nozzle furnished with regenerative cooling system, gas generator, turbo pump unit comprising turbine, multi-component gas generator, oxidiser and fuel pumps. In compliance with this invention four-component gas generator running on oxidiser, first fuel, second fuel in liquid phase and second fuel in gaseous phase. Note that turbo pump unit comprises first fuel pump, second fuel pump and second fuel extra pump intended for consecutive operation on first and second fuels without changing oxidiser. Note also that second fuel pump and second fuel extra pump are arranged directly below oxidiser pump and communicate via shut-off valves with main fuel manifold and gas generator. Engine comprises control unit connected with all valves. Drain line incorporating drain valve is connected ahead of second fuel shut-off valve. Temperature pickup connected with control unit is arranged ahead of aforesaid drain valve. Proposed method comprises feeding oxidiser and fuel into at least gas generator and combustion chamber, their ignition and forcing out combustion products through jet nozzle. Note here that after burning the first fuel, second fuel is fed into gas generator and every combustion chamber. Liquid oxygen is used as oxidiser, carbon fuel is used as first fuel and liquid hydrogen is used as second fuel. Prior to feeding second fuel, fuel pipelines and regenerative cooling system of every nozzle are blown off by inert gas to remove residues of the first fuel. Prior to feeding second fuel into gas generator and combustion chamber, second fuel pump and second fuel extra pump are cooled by forcing second fuel through drain valve to produce liquid phase in drain pipeline, which is controlled by temperature pickup arranged ahead of drain valve. After cutting off the engine, regenerative cooling system of every nozzle is blown off by inert gas to remove residues of second fuel.

EFFECT: higher reliability and increased power output.

9 cl, 4 dwg

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RU 2 386 844 C1

Authors

Bolotin Nikolaj Borisovich

Dates

2010-04-20Published

2008-12-18Filed