ROCKET ENGINE, ROCKET, AND METHOD FOR STARTING ROCKET ENGINE

A rocket engine is provided with a fuel flow path (31-39), a catalyst part (51), a turbine (12), a first pump (11), a combustion chamber (21), and a nozzle (22). Hydrocarbon-based fuel flows through the fuel flow path (31-39). The catalyst part (51) is provided in the middle of the fuel flow path (3...

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Bibliographic Details
Main Authors OBASE KIMIHITO, KAWAMATA YOSHIHIRO
Format Patent
LanguageEnglish
French
German
Published 28.10.2015
Subjects
AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
COSMONAUTICS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
PERFORMING OPERATIONS
TRANSPORTING
VEHICLES OR EQUIPMENT THEREFOR
WEAPONS
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Summary:A rocket engine is provided with a fuel flow path (31-39), a catalyst part (51), a turbine (12), a first pump (11), a combustion chamber (21), and a nozzle (22). Hydrocarbon-based fuel flows through the fuel flow path (31-39). The catalyst part (51) is provided in the middle of the fuel flow path (31-39), and gasifies the fuel. The turbine (12) is driven by the gasified fuel. The first pump (11) supplies the fuel to the fuel flow path (31-39) by the driving of the turbine (12). The combustion chamber (21) burns the gasified fuel supplied from the fuel flow path (31-39), and an oxidizing agent. The nozzle (22) delivers combustion gas in the combustion chamber (21) and is cooled by heat exchange with part of the fuel flow path (31-39).
Bibliography:Application Number: EP20140753901