SYSTEM OF STABILIZATION OF RELATIONSHIP OF PROPELLANT COMPONENT FLOW RATES IN LIQUID-PROPELLANT ROCKET ENGINE

摘要

FIELD: liquid propellant rocket engines with afterburning of generator gas in combustion chamber. SUBSTANCE: system contains flow rate Venturi tubes fitted in lines of both propellant components, sensitive elements connected to these tubes and provided with flexible comparing members and nozzles which may be closed, adjusting jet and flow rate restrictor fitted in line of one of propellant component and provided with piston-type hydraulic servomotor. Sensitive element is divided into two chamber by means of comparing member: one chamber is free and is brought in communication with throat section of Venturi tube and other chamber contains nozzle. Chamber of sensitive element where Venturi tube is located is connected with inlet of this tube through jet. Outlet of nozzle contained in above-mentioned chamber is brought in communication with similar chamber of other sensitive element through jet; nozzle of this sensitive element is connected with low-pressure line by its outlet. Servomotor is provided with hydraulic booster whose working chambers are brought in communication with inlet of Venturi tube fitted in line being restricted and with outlet of nozzle of sensitive element of other tube. EFFECT: enhanced efficiency. 1 dwg