ROCKET ENGINE SYSTEM FOR REALIZING HIGH-SPEED RESPONSE

Title:

ROCKET ENGINE SYSTEM FOR REALIZING HIGH-SPEED RESPONSE

Document Type and Number:

WIPO Patent Application WO/2011/030719

Kind Code:

A1

Abstract:

Disclosed is a turbo pump wherein 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 so that an equivalent region between a turbine efficiency curve obtained on the basis of a conditional expression to maintain the number of rotations of the rotary shaft constant without depending on the flow rate of a pump and a turbine efficiency curve obtained from an actual turbine, corresponds to an operation region.

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Inventors:

MORI HATSUO (JP)
NARUO YOSHIHIRO (JP)
TOKUDOME SHINICHIRO (JP)
YAGISHITA TSUYOSHI (JP)
YAMAMOTO TAKAYUKI (JP)
INATANI YOSHIFUMI (JP)

Application Number:

PCT/JP2010/065124

Publication Date:

March 17, 2011

Filing Date:

September 03, 2010

Export Citation:

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Assignee:

IHI CORP (JP)
JAPAN AEROSPACE EXPLORATION (JP)
MORI HATSUO (JP)
NARUO YOSHIHIRO (JP)
TOKUDOME SHINICHIRO (JP)
YAGISHITA TSUYOSHI (JP)
YAMAMOTO TAKAYUKI (JP)
INATANI YOSHIFUMI (JP)

International Classes:

F02K9/46; F01D15/08; F02K9/44; F02K9/56

Foreign References:

JPH11229963A	1999-08-24
JPH10238408A	1998-09-08
JP2003148250A	2003-05-21
JP2007016781A	2007-01-25
JP2002538346A	2002-11-12
JP2008267385A	2008-11-06
JP2009207480A	2009-09-17
JPH11229963A	1999-08-24

Other References: