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

FIELD: rocket manufacture. SUBSTANCE: engine includes chamber, gas generator, oxidizer and propellant turbo-pump unit including turbine and pumps. Booster turbo-pump units are mounted before oxidizer pump and fuel pump. Wheel of hydraulic turbine of one of them is secured on peripheral portion of blades of axial-and-diagonal impeller of pump. hydraulic turbine is provided with working and starting nozzles and starting liquid supply main. Used as starting liquid in hydraulic turbines is component of propellant similar to that fed by pump of booster turbo-pump unit. Starting liquid supply main in engine of rocket first stage is connected to ground-based system. Starting liquid supply mains in engines of upper stages of rocket are provided with starting bottles filled with respective component of propellant. Starting bottles are provided with pressurizing gas supply pipe lines. Starting bottle with propellant is located in propellant tank in engines working on cryogenic propellants. EFFECT: increased pressure at pump inlet of turbo-pump unit in starting the engine due to preliminary spinning the rotors of booster units by means of working hydraulic turbine; effective cooling of structure. 4 cl, 5 dwg