发明名称 |
Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine |
摘要 |
A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet. |
申请公布号 |
EP2103799(A3) |
申请公布日期 |
2013.06.26 |
申请号 |
EP20080162393 |
申请日期 |
2008.08.14 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
KIMURA, TATSUYA;KAWAMATA, YOSHIHIRO;NIU, KENICHI |
分类号 |
F02K9/97;F02K1/38;F02K9/40;F02K9/48;F02K9/82 |
主分类号 |
F02K9/97 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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