FIELD: rocketry.
SUBSTANCE: invention relates to liquid propellant rocket engine operating on cryogenic oxidizer and hydrocarbon fuel. Proposed liquid-propellant rocket engine contains combustion chamber with regenerative cooling duct, turbopump set with main turbine and oxidizer and fuel pumps in which fuel pump output is connected through fuel valve with combustion chamber and oxidizer pump output is connected through oxidizer valve with gas generator installed over combustion chamber. Turbopump set contains additional set contains additional fuel pump whose input is connected with output of fuel pump, and output is connected with gas generator by high-pressure pipeline in which high-pressure valve and flow rate regulator are installed. Shafts of additional fuel pump is connected though step-up gear with shafts of turbopump set.
EFFECT: improved reliability, increased power output and specific characteristics of liquid propellant rocket engine, reduced weight of engine.
6 cl, 11 dwg
| Title | Year | Author | Number |
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