ROCKET ENGINE, ROCKET AND START METHOD OF ROCKET ENGINE

摘要

A rocket engine has fuel passage of pipes 31-39, a catalyst section 51, a turbine 12, a first pump 11, a combustion chamber 21 and a nozzle 22. The fuel passage of pipes 31-39 supply the hydrocarbon fuel. The catalyst section 51 is provided on the way of the fuel passage of pipes 31-39 to gasify the fuel. The turbine 12 is driven with the gasified fuel. The first pump 11 supplies the fuel to the fuel passage of pipes 31-39 through the drive by the turbine 12. The combustion chamber 21 combusts the gasified fuel supplied from the fuel passage of pipes 31-39 and the oxidizer. The nozzle 22 sends out the combustion gas from the combustion chamber 21, and it is heat-exchanged with a part of the fuel passage of pipes 31-39.

主权项

1. A rocket engine comprising:
a fuel passage through which a hydrocarbon fuel flows; a catalyst section provided on a way of the fuel passage to gasify the fuel; a turbine provided on the way of the fuel passage and driven with the gasified fuel; a first pump configured to supply the fuel to the fuel passage through a drive by the turbine; a combustion chamber configured to combust the gasified fuel supplied through the fuel passage by using an oxidizer; and a nozzle configured to send out the combustion gas and carry out heat exchange with a part of the fuel passage to be cooled. wherein the catalyst section is provided inside the fuel passage in a location where the heat exchange is carried out.