LIQUID-PROPELLANT ROCKET ENGINE FUEL LINE Russian patent published in 2004 - IPC

FIELD: rocketry.

SUBSTANCE: proposed fuel line of liquid-propellant rocket engine contains centrifugal pump arranged in inlet part of fuel line, chamber cooling jacket duct arranged in outlet part of fuel line including duct of chamber nozzle part cooling jacket and duct of combustion chamber cooling jacket, and also automatic control devices. Said automatic control devices include at least two multiple-action valves, for instance, pneumatically controlled valves, one of which is installed at inlet of fuel line and the other, in its outlet part. Duct of chamber nozzle part cooling jacket is connected to duct of combustion chamber cooling jacket through valve installed in outlet part of fuel line. Passive inlet of ejector is connected to fuel line, and active inlet of ejector is connected to reservoir with inert gas or nitrogen, outlet of ejector being connected with drain line, for instance, into atmosphere.

EFFECT: improved reliability of starting of booster liquid-propellant rocket engine of high thrust owing to prevention of formation of large volume of gas bubbles in fuel line.

10 cl, 1 dwg