发明授权
- 专利标题： Rocket engine system for realizing high-speed response
- 专利标题（中）： 火箭发动机系统实现高速响应
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申请号： US13394843申请日： 2010-09-03
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公开(公告)号： US08943795B2公开(公告)日： 2015-02-03
- 发明人: Hatsuo Mori , Yoshihiro Naruo , Shinichiro Tokudome , Tsuyoshi Yagishita , Takayuki Yamamoto , Yoshifumi Inatani
- 申请人： Hatsuo Mori , Yoshihiro Naruo , Shinichiro Tokudome , Tsuyoshi Yagishita , Takayuki Yamamoto , Yoshifumi Inatani
- 申请人地址： JP JP
- 专利权人： IHI Corporation,Japan Aerospace Exploration Agency
- 当前专利权人： IHI Corporation,Japan Aerospace Exploration Agency
- 当前专利权人地址： JP JP
- 代理机构： Ostrolenk Faber LLP
- 优先权： JPP2009-207480 20090908
- 国际申请： PCT/JP2010/065124 WO 20100903
- 国际公布： WO2011/030719 WO 20110317
- 主分类号： F02K9/46
- IPC分类号： F02K9/46 ; F04D13/02
摘要：
Disclosed is a turbo pump in which a pump impeller is connected to one end of a rotary shaft and a turbine is connected to the other end of the rotary shaft. The turbo pump is designed such that an equivalent region, between a turbine efficiency curve obtained on the basis of a conditional expression where the number of rotations of the rotary shaft is maintained constant regardless of a pump flow rate and a turbine efficiency curve of an actual machine, becomes an operation region.
公开/授权文献
- US20120167552A1 ROCKET ENGINE SYSTEM FOR REALIZING HIGH-SPEED RESPONSE 公开/授权日：2012-07-05
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