FIELD: transport.
SUBSTANCE: invention relates to aerospace engineering and can be used for cooling the liquid-propellant rocket engine nozzle supersonic section. Invention aims at developing a serviceable nozzle supersonic section cooler with lower coolant pressure (Pcool<<Pc) to produce high efficiency liquid-propellant rocket engines with increased chamber pressure, simplifying the nozzle design and increasing their efficiency. Target is hit by incorporating a check valve in heat carrier circulation line at main line communicating nozzle supersonic section cooling circuit outlet with turbine inlet and connecting heat carrier tank with valve with said main line at section between check valve and turbine. Besides, exhaust pipe with valve or receiver is connected at main line section between nozzle supersonic section and check valve.
EFFECT: higher reliability and efficiency, lower costs.
2 dwg
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