LIQUID-PROPELLANT ROCKET ENGINE PLANT Russian patent published in 1999 - IPC

FIELD: recoverable single-stage oxygen-hydrogen launch vehicles. SUBSTANCE: engine plant includes tanks for propellant components and modular combustion chambers located under fairings over periphery of load-bearing circular frame. External expansion nozzle of plant is made in form of truncated central body with cooling jacket. Oxidizer and fuel turbo-pump units are self-contained. Central body is used bottom of one of tanks. Turbo-pump units of one propellant component of this tank are mounted on shear of central body and pump are located inside tank. Turbo-pump units of other component of propellant are located over periphery of load-bearing circular frame. Drive of turbines of turbo-pump units of one component is effected by means of open-loop gas generators and drive of turbines of turbo-units of other components is effected in closed without gas generators. EFFECT: reduced mass of plant; enhanced reliability and increased service life of engine plant due to combination open-closed propellant feed system. 4 cl, 1 tbl