LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2002 - IPC

FIELD: spacecraft; rocket engines. SUBSTANCE: proposed liquid-propellant rocket engine is designed for use in cryogenic stages of launch vehicles and as cruise engines of spacecraft. It includes combustion chamber with regenerative cooling duct, evaporator, fuel and oxidizer pumps, and turbine. Outlet of pump of one of components (fuel or oxidizer) is connected by main line with inlet of coolant line of evaporator, and outlet of evaporator at the same line is connected with inlet of turbine. Outlet of pump of other component communicates with combustion chamber. Engine includes also condenser, intermediate coolant source with controllable valve, intermediate coolant circulating pump with intermediate coolant turbine. Inlet of evaporator at heat carrier line is connected with outlet of intermediate coolant turbine. Outlet of evaporator at heat carrier line is connected with intermediate coolant source by means of controllable valve, and with inlet of intermediate coolant circulating pump. Outlet of intermediate coolant circulating pump is connected with inlet of combustion chamber regenerative cooling duct, and outlet of duct is connected with inlet of intermediate coolant turbine. Inlet of condenser at cooling agent line is connected with outlet of pump of one of components, and outlet of the same line is connected with combustion chamber. Inlet and outlet of condenser at heat carrier line are connected, respectively, with outlet of turbine and inlet of pump of the component. EFFECT: improved efficiency of liquid-propellant rocket engine, enlarged operating capabilities. 1 dwg