| 双出口气膜孔冷却效率实验 |
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| 引用本文： | 李广超,凌旭,寇志海,吴超林,张魏.双出口气膜孔冷却效率实验[J].航空动力学报,2014,29(5):1029-1035. |
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| 作者姓名： | 李广超 凌旭 寇志海 吴超林 张魏 |
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| 作者单位： | 沈阳航空航天大学 航空航天工程学部 辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136;沈阳航空航天大学 航空航天工程学部 辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136;沈阳航空航天大学 航空航天工程学部 辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136;沈阳航空航天大学 航空航天工程学部 辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136;沈阳航空航天大学 航空航天工程学部 辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136 |
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| 基金项目： | 国家自然科学基金（51306126）；航空科学基金（2012ZB54006） |
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| 摘 要： | 为了进一步理解双出口气膜孔的冷却特性,建立了气膜冷却效率实验台,通过红外测温技术研究了圆孔和4个不同次孔方位角的双出口孔在吹风比为0.3~2.0时的冷却效率.结果表明:和圆孔相比,次孔方位角为30°,45°,60°双出口孔能提高面平均冷却效率18%~37%.次孔方位角为30°双出口孔在低吹风比下提高冷却效率最显著,次孔方位角为60°双出口孔在高吹风比下提高冷却效率最显著.在研究的吹风比范围内,次孔方位角为45°双出口孔都能较显著地提高冷却效率,次孔方位角为75°双出口孔冷却效率低于圆孔冷却效率.
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| 关 键 词： | 航空发动机 涡轮叶片 气膜冷却 冷却效率 双出口孔 |
| 收稿时间： | 2013/3/10 0:00:00 |
Experiment of cooling effectiveness with double-outlet film hole |
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| LI Guang-chao,LING Xu,KOU Zhi-hai,WU Chao-lin and ZHANG Wei.Experiment of cooling effectiveness with double-outlet film hole[J].Journal of Aerospace Power,2014,29(5):1029-1035. |
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| Authors: | LI Guang-chao LING Xu KOU Zhi-hai WU Chao-lin and ZHANG Wei |
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| Institution: | Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China;Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China;Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China;Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China;Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China |
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| Abstract: | In order to understand the cooling characteristics of the double-outlet film holes further,the platform for testing film cooling effectiveness was established.The cooling effectiveness of the cycle holes and four kinds of double-outlet holes with various orientation angles was studied at the blowing ratios from 0.3 to 2.0 by infrared measurement.The results show that:compared with the cycle hole,the surface averaged cooling effectiveness of the double-outlet holes is improved by 18%-37% with 30,45 and 60 degrees of orientation angles.At the low blowing ratios,the cooling effectiveness of the double-outlet holes with 30 degree of orientation angles is most significantly improved.At the high blowing ratios,the cooling effectiveness of double-outlet holes with 60 degree of orientation angles is most significantly improved.The double-outlet holes with 45 degree orientation angles can significantly improve the cooling effectiveness at both high and low blowing ratios.The cooling effectiveness of the double-outlet holes with 75 degree of orientation angles is lower than that of the cylindrical holes. |
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| Keywords: | aero-engine turbomachine blades film cooling cooling effectiveness double-outlet hole |
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