FIELD: engines and pumps.
SUBSTANCE: invention can be used in the design of liquid-propellant rocket engines (LRE). Rocket engine comprises a combustion chamber with the path of cooling and the nozzle head, steam-gas generator, a turbopump unit comprising an oxidant pump, fuel pump, water pump, a turbine, which input communicates with the outlet of the cooling path, and output - with the nozzle head, an additional turbine, with this output is steam-gas generator in communication with the input of an additional turbine and its output more turbines installed exhaust pipe at the outlet of which there is a nozzle.
EFFECT: improving energy performance and reliability of the LPRE.
1 dwg
