发明授权
- 专利标题： Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine
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申请号： EP08162393.6申请日： 2008-08-14
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公开(公告)号： EP2103799B1公开(公告)日： 2018-05-23
- 发明人: Kimura, Tatsuya , Kawamata, Yoshihiro , Niu, Kenichi
- 申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
- 申请人地址： 16-5, Konan 2-chome, Minato-ku Tokyo 108-8215 JP
- 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： 16-5, Konan 2-chome, Minato-ku Tokyo 108-8215 JP
- 代理机构： Studio Torta S.p.A.
- 优先权： JP2008069502 20080318
- 主分类号： F02K9/97
- IPC分类号： F02K9/97 ; F02K9/40 ; F02K9/48 ; F02K9/82 ; F02K1/38
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.
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