FIELD: transport.
SUBSTANCE: invention relates to space engineering. Starting system relates to liquid-propellant rocket engine including cryogenic fuel tank 1, turbo pump units 2, 6, gas generator 7 communicated with turbine 18 of turbo pump unit 6, combustion chamber 19 and nozzle 20. System is equipped with high-pressure cylinders 3 with charging valve 17. Additionally, it comprises service pipeline 14 its inlet being communicated with tank 1 and outlet being connected to combustion chamber nozzle jackets 8, 9. Besides, it includes pipeline 5 to feed gaseous cryogenic fuel from nozzle jacket 9 to turbine 9 of the unit feeding fuel to gas generator 7. Pipeline 5 is connected via starting valve 16 with cylinders 3. Besides, system is equipped with makeup fuel pipeline 21 with valve 15 to communicate combustion chamber jacket 8 with cylinders 3. Systems serves to start rocket engine and to charge cylinder 3 via pipeline 21 with cryogenic fuel vapor from jacket 8. There is no need in special means of nozzle inner wall cooling.
EFFECT: ten percent decrease in engine weight.
1 dwg
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