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	Analysis of the subsection design of the porous wall of a transpiration cooling nozzle
	Jin Shao-shan ; Jiang Pei-xue ; Sun Ji-Guo
	2010-10-12 ; 2010-10-12
关键词	Theoretical or Mathematical/ aerodynamics coolants nozzles numerical analysis rockets/ transpiration cooling rocket nozzle coolant flow porous media wall Fluent code gas flow/ E2200 Mechanical components, systems and devices E2130 Fluid mechanics and aerodynamics (mechanical engineering) E0210L Numerical analysis
中文摘要	In order to minimize the coolant flow for transpiration cooling rocket nozzle with sintered porous media wall, an optimized transpiration cooling structure was presented in this paper, whose porous wall was divided into several sections along the axis direction. The transpiration cooling for a thruster with four-section structure porous wall was numerically studied by Fluent code and the results were compared with those of the one-section structure transpiration thruster. The results show that four-section structure can decrease the ratio of coolant flow and gas flow from 28.3% to 12.6% on the premise of satisfying the cooling need of the nozzle inner surface wall, the multi-section porous wall design is an effective way to reduce nozzle transpiration coolant flow.
语种	中文
出版者	Editorial Department of the Journal of Aerospace Power ; China
内容类型	期刊论文
源URL	[http://hdl.handle.net/123456789/79944]
专题	清华大学
推荐引用方式 GB/T 7714	Jin Shao-shan,Jiang Pei-xue,Sun Ji-Guo. Analysis of the subsection design of the porous wall of a transpiration cooling nozzle[J],2010, 2010.
APA	Jin Shao-shan,Jiang Pei-xue,&Sun Ji-Guo.(2010).Analysis of the subsection design of the porous wall of a transpiration cooling nozzle..
MLA	Jin Shao-shan,et al."Analysis of the subsection design of the porous wall of a transpiration cooling nozzle".(2010).

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