| 液晶测温法对平板气膜冷却的实验研究 |
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| 引用本文： | 徐国强,田宁,陶智,丁水汀,罗翔,邓宏武.液晶测温法对平板气膜冷却的实验研究[J].航空动力学报,2007,22(5):704-708. |
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| 作者姓名： | 徐国强 田宁 陶智 丁水汀 罗翔 邓宏武 |
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| 作者单位： | 北京航空航天大学,航空发动机气动热力重点实验室,北京,100083 |
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| 基金项目： | 教育部跨世纪优秀人才培养计划
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高等学校博士学科点专项科研项目 |
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| 摘 要： | 采用热色液晶测温法,对沿流向倾角30°的圆孔排平板气膜冷却进行了实验研究.测量了绝热壁温、壁温等温度场.研究了吹风比、孔排等因素对气膜冷却效果和换热系数的影响.结果表明:吹风比对气膜冷却效果的影响很大,冷却效果随吹风比的增大而降低;圆孔气膜冷却效果沿横向位置波动较大,孔之间容易形成冷却死区.利用液晶测温技术可以很好地反映气膜冷却区域及冷却效果等.
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| 关 键 词： | 航空、航天推进系统 平板气膜冷却 吹风比 热色液晶 冷却效果 液晶测温法 平板气膜冷却 实验 研究 film cooling surface flat research 区域 液晶测温技术 利用 死区 波动 位置 圆孔 结果 影响 换热系数 冷却效果 因素 |
| 文章编号： | 1000-8055(2007)05-0704-05 |
| 收稿时间： | 5/8/2006 12:00:00 AM |
| 修稿时间： | 2006年5月8日 |
Experimental research on flat surface film cooling by TLC |
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| XU Guo-qing,TIAN Ning,TAO Zhi,DING Shui-ting,LUO Xiang and DENG Hong-wu.Experimental research on flat surface film cooling by TLC[J].Journal of Aerospace Power,2007,22(5):704-708. |
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| Authors: | XU Guo-qing TIAN Ning TAO Zhi DING Shui-ting LUO Xiang and DENG Hong-wu |
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| Institution: | National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;National Key Laboratory on Aero-engines, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China |
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| Abstract: | The performance of flat surface film cooling with 30° film cooling holes along streamwise was experimentally investigated using thermal liquid crystal.The temperature fields of adiabatic wall and conductive wall were measured.The effects of blow ratio and rows on film cooling effectiveness and heat transfer coefficient was studied.The results show that:blow ratio is a main influential factor to the film cooling effectiveness,the film cooling effectiveness decreases with the increasing of blow ratio;the film cooling effectiveness of discrete holes fluctuate dramatically across the transverse section,and dead zone is prone to occur between two discrete holes.TLC technique can be successfully applied to reflect film cooling effectual area and cooling effect. |
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| Keywords: | aerospace propulsion system film cooling blow ratio TLC(thermal liquid crystal) effectiveness |
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