A principle of liquid propellant rocket engine operation and a liquid propellant rocket engine

RU patent № 2187684

The principle of liquid propellant rocket engine consists in feeding propellants to the engine combustion chamber, gasification of one of components in the combustion chamber cooling passage, its supply to the turbine of turbopump unit and subsequent discharge to the injector head of combustion chamber. A part of the flow of one of propellant components is directed to the combustion chamber, the rest gasified and fed to turbines of turbopump units. The gaseous component spent on turbines is mixed with the liquid component coming to the engine at a pressure exceeding the pressure of saturated vapors of the obtained mixture.
The proposed liquid propellant rocket engine comprises a combustion chamber with a regenerative cooling passage, propellants pumps, and a turbine. The engine comprises a pump of the boost turbopump unit and a mixer which are installed in series upstream of the pump of the main turbopump unit for supplying one of propellant components. The exit of the main turbopump unit pump is connected to the injector head of the combustion chamber as well as to the regenerative cooling passage of the combustion chamber. In its turn the regenerative cooling passage is connected to turbines of the main and boost turbopump units which exits are connected to the mixer.
The invention enables the reliability of the liquid propellant rocket engine to be increased and mass-and-energy characteristics of liquid propellant rocket engine to be improved.