HYBRID ROCKET ENGINE Russian patent published in 2008 - IPC F02K9/72 

FIELD: engines and pumps.

SUBSTANCE: proposed hybrid rocket engine incorporates a compartment accommodating liquid fuel component tank and feed system, combustion chamber housing, solid propellant charge, nozzle. At that the working gas regeneration and bleed system to drive the turbo-pump unit (TPU) comprises a bleeder-gas generator mounted on the nozzle bottom and nozzle with its inlet cooled gas duct tightly and rigidly fitted in the combustion chamber housing inserted element and, at the same time, in the bleeder-gas generator manifold. The said bleeder-gas generator liquid fuel component inlet communicates with the liquid component pump outlet branch pipe via a line accommodating an assembly of hydraulic automatic control. Note that the said bleeder-gas generator outlet communicates, via a line, with the turbine inlet manifold that features a gas communication with the auxiliary engines. Note also that the aforesaid turbine outlet manifold represents a cryogenic heat exchanger with its inlet receiving the liquid component via the line accommodating the aforesaid hydraulic automatic control assembly and communicating with the liquid component pump outlet branch pipe, while its outlet is coupled with the gasified component feed duct with a supercharger arranged inside the liquid component tank.

EFFECT: higher efficiency, stability and reliability of hybrid engine turbo-pump unit, use of turbine exhaust gas in gas turbine engine auxiliary devices.

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