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 engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and turbopump unit comprising turbine, oxidiser pump and fuel pumps. It differs from known designs in that said turbopump unit comprises two fuels pumps and two extra fuel pumps designed to operate on first fuel and second fuel. Note here that second fuel pump and additional second fuel pump are arranged below oxidiser pump. Downstream of fuel pumps, first and second fuel valves are arranged connected, via electric line, with synchronisation device. Proposed engine incorporates also control unit connected with aforesaid synchronisation device. 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: improved operating performances of liquid propellant engine in wide range of flight conditions at various altitudes.
5 cl, 3 dwg
