旋转条件下“冲击/出流”双层壁内部换热实验

徐磊; 常海萍; 潘金栋

旋转条件下“冲击/出流”双层壁内部换热实验

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2006-09-19
- 修回日期: 2006-12-25
- 刊出日期: 2007-10-28

Experimental research on heat transfer of "impingement/effusion" double-plate configuration in rotating state

College of Energy and Power Engineering, Nanjing University ofAeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 以高效航空发动机涡轮叶片内部冷却为研究背景,在旋转条件下对带气膜出流的双层壁内部冲击换热特性进行了研究.实验在旋转与冲击方向相同和相反两种情况下进行,得到了冲击雷诺数Rej(5 000～10 000)、旋转数Ro(0～0.003 532)、无因次温比(Tw-Tf)/Tw(0.061～0.136)的变化对冲击靶面换热特性的影响规律;通过对"双层壁"的实验结果与常规"冲击/气膜"冷却结构的实验结果的比较发现,在不同的流动和旋转状态下,前者换热能力强于后者15%以上.
- 航空、航天推进系统 /
- 旋转 /
- 涡轮叶片 /
- 气膜冷却 /
- 冲击冷却
Abstract: Based on the internal cooling turbine blade of high-performance aeroengine, the internal heat transfer characteristics of double-plate configuration with film cooling have been carried out in rotating state.The test was performed in the same and opposite direction of rotation.Thus, the effect of jet Reynolds numbers Rej(5 000～10 000), rotation numbers Ro(0～0.003 532)and wall-to-jet temperature difference ratios(Tw-Tf)/Tw(0.061～0.136)on heat transfer characteristics of impingement was obtained.By comparing the experiment results of both double-plate configuration and general configuration of impingement/effusion structure, it is observed that the heat transfer of double-plate configuration is 15% stronger than that of general configuration.
- aerospace propulsion system /
- rotation /
- turbine blade /
- film cooling /
- impinging cooling

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参考文献(10)

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