小空间内冲击/气膜复合冷却换热特性试验

毛军逵; 郭文; 常海萍; 徐磊; 张镜洋; 常国强

小空间内冲击/气膜复合冷却换热特性试验

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国燃气涡轮研究院涡轮室, 成都 610500

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出版历程
- 收稿日期: 2006-02-24
- 修回日期: 2006-07-31
- 刊出日期: 2007-03-28

Experimental investigation of the local heat transfer of impinging cooling with outflow film in closed small space

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Turbine Group, China Gas Turbine Establishment, Chengdu 610500, China

摘要

摘要: 利用相似理论的原理, 试验研究了封闭小空间内冲击/气膜复合冷却内表面的换热特性.研究中通过改变冲击Re数（10000⁴0000）、冲击距离H和冲击孔直径D之比H/D（0.17².0）, 在2种冲击孔和气膜孔间距P和冲击孔直径D之比P/D（0, 1）条件下, 细致分析冲击Re数、H/D对复合冷却内表面局部换热特性的影响.结果表明, 在本文的试验工况中, 冲击靶板上的局部Nu数随着冲击Re的增加而不断变大, 而Nu数随着H/D的变化规律并非单调.当P/D=0, H/D=2时换热效果达到最佳;P/D=1时, 在X/D=±3范围内, 小冲击Re数条件下H/D=0.17和H/D=2的换热效果比较接近, 大冲击Re数条件下H/D=1和H/D=2的换热效果比较接近.
- 航空、航天推进系统 /
- 换热 /
- 冲击 /
- 复合冷却
Abstract: Experiments were carried out to investigate the heat transfer of compound cooling（impinging cooling with outflow film）.Local heat transfer coefficients on inner surface were obtained over a Reynolds number range of 10 000～40 000,nozzle-to-plate spacing H/D range of 0.17～2.0,the ratio between impinging jet and film hole distance to jet hole diameter P/D range of 0 and 1.Experimental results show that the local heat transfer coefficient was affected by impingement Reynolds number and nozzle-to-plate spacing greatly.Under the parameters in this paper,the local Nu number increased with the impingement Reynolds number.When P/D=0,the maximum Nu number was achieved while H/D=2.When P/D increased to unity,the maximum Nu number was gotten while H/D=2 and 0.17 under lower impingement Reynolds number.And this proper value of H/D will change to be 2 and 1 under higher impingement Reynolds number.
- aerospace propulsion system /
- heat transfer /
- impinging /
- compound cooling

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参考文献(8)

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