发明名称 |
ROCKET ENGINE, ROCKET, AND METHOD FOR STARTING ROCKET ENGINE |
摘要 |
<p>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).</p> |
申请公布号 |
WO2014129419(A1) |
申请公布日期 |
2014.08.28 |
申请号 |
WO2014JP53611 |
申请日期 |
2014.02.17 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
KAWAMATA YOSHIHIRO;OBASE KIMIHITO |
分类号 |
F02K9/64;B64G1/00;F02K9/46;F02K9/68 |
主分类号 |
F02K9/64 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|