LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2015 - IPC F02K9/42 F02K9/54 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in production of liquid-propellant engines. This engine comprises four chambers, turbopump unit, gas generator, oxidiser and propellant booster turbopump units, oxidiser and propellant lines, blowing and control systems, control and adjustment units and bellows in gas ducts. Filters with screens of filtering fineness of 0.03-0.05 mm and mesh diameter of 0.13-0.2 mm are arranged in engine lines upstream of said oxidiser and propellant booster turbopump units, in turbopump unit axial unloading control unit upstream of gas generator oxidiser inlet. Said filters stop the impurity particles of diameters larger than the filter large meshes and feature the total filtering area larger than the line or pipe ID some 1.5-2 times. Besides, it exploits the cooled bellows arranged gas ducts of flexible pipes units while grating is arranged at the starting cylinder inlet. Screen filters are located at control system inlet and outlet of electrically driven air valves. Filter is located in propellant feed line while two filters are arranged at propellant inlet into combustion chamber head.

EFFECT: higher reliability of engine systems and units.

6 cl, 21 dwg