发明申请
US20090235639A1 ROCKET NOZZLE AND CONTROL METHOD FOR COMBUSTION GAS FLOW IN ROCKET ENGINE
有权
ROCKET喷嘴和控制方法用于燃烧气体在流体发动机中的流动
- 专利标题： ROCKET NOZZLE AND CONTROL METHOD FOR COMBUSTION GAS FLOW IN ROCKET ENGINE
- 专利标题（中）： ROCKET喷嘴和控制方法用于燃烧气体在流体发动机中的流动
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申请号： US12200265申请日： 2008-08-28
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公开(公告)号： US20090235639A1公开(公告)日： 2009-09-24
- 发明人: Tatsuya KIMURA , Yoshihiro KAWAMATA , Kenichi NIU
- 申请人： Tatsuya KIMURA , Yoshihiro KAWAMATA , Kenichi NIU
- 申请人地址： JP Tokyo
- 专利权人： MITSUBISHI HEAVY INDUSTRIES, LTD.
- 当前专利权人： MITSUBISHI HEAVY INDUSTRIES, LTD.
- 当前专利权人地址： JP Tokyo
- 优先权： JP2008-069502 20080318
- 主分类号： F02K9/08
- IPC分类号： F02K9/08
摘要：
A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.
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