FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operated on three fuel components, i.e. cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed rocket comprises first- and second-stage rocket units connected in parallel, oxidiser and fuel tanks coupled by power assemblies and equipped with at least one first-stage engine and one second-stage engine. In compliance with this invention, second-stage unit comprises second fuel tank, every second-stage engine incorporates combustion chamber and fuel feed turbopump unit. Proposed engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and two turbopump units comprising turbine, oxidiser pump and fuel pumps. In compliance with this invention, outlets of all pumps communicate, via gas duct, with gas generator outlet communicates with every combustion chamber. Method of operation of above described engine comprises feeding fuel and oxidiser into gas generator and combustion chamber, igniting them and exhausting combustion products via jet nozzle. In compliance with this invention, first fuel utilised, second fuel is fed into gas generator and combustion chamber. Prior to feeding second fuel, fuel pipelines and nozzle regenerative cooling systems are blown down to remove first fuel residues.
EFFECT: higher thrust-to-weight ratio, improved operating performances.
12 cl, 8 dwg
