边倒圆型气膜孔流动换热特性研究

推进技术 ›› 2018, Vol. 39 ›› Issue (5): 1067-1076.

边倒圆型气膜孔流动换热特性研究

孟通¹,朱惠人¹,刘存良¹,周申平²

西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,中国航发湖南动力机械研究所，湖南株洲 412002

发布日期:2021-08-15
作者简介:孟通，男，博士生，研究领域为航空发动机高温部件热防护。E-mail: mengtong1989@163.com 通讯作者:朱惠人，男，博士，教授，研究领域为航空发动机高温部件热防护。
基金资助:
国家重点基础研究发展计划资助项目(2013CB035702)。

Experimental and Numerical Study on Film Cooling Performance of Radiusing-Type Hole

School of Power and Energy，Northwestern Ploytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Ploytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Ploytechnical University，Xi’an 710072，China and AECC Hunan Aviation Powerplant Research Institute，Zhuzhou 412002，China

Published:2021-08-15

摘要/Abstract

摘要： 为提高涡轮叶片气膜冷却效率，根据主流与射流间的相互作用关系，并以圆柱型气膜孔为基础，在气膜孔出口前缘位置进行边倒圆处理，同时对该新型的边倒圆型气膜孔结构进行了实验及数值计算研究。分析了边倒圆型气膜孔的流动换热机理，得到了新型气膜孔下游全表面气膜冷却特性分布及气膜孔的流量系数。结果表明:边倒圆型气膜孔内流动均匀，出口涡强度有所降低，进而能够减弱主流通道内的反转对涡强度；同时由于边倒圆孔的扩张作用使得射流法向动量降低、展向动量增强，从而提高气膜冷却效率。边倒圆型气膜孔的孔下游区域气膜贴壁性较好，气膜展向覆盖面积较大。相比于圆柱型气膜孔，边倒圆型气膜孔下游区域换热系数较高，远孔区域换热系数较小。新型气膜孔的流量系数比圆柱型气膜孔约大5%，孔内流动损失较小。整体上看，边倒圆型气膜孔具有较好的流动换热特性。

关键词: 涡轮叶片；气膜冷却；边倒圆型气膜孔；实验研究；数值模拟

Abstract: In order to get higher film cooling performance， a new structure called radiusing-type hole was proposed based on cylinder hole and the interaction between mainstream and jet of film cooling. Medication of radiusing was used near the leading edge of film cooling hole. Experiments and numerical simulations were conducted to figure out the flow and heat transfer performance of radiusing-type hole. Film cooling characteristics downstream of the hole and discharge coefficient were studied. Results show that flow structure within the radiusing-type hole is more uniform than cylindrical hole which leads to weaker kidney vortex pairs in main flow. Normal momentum of jet is weaker and lateral momentum is stronger because of the expanding effect of radiusing-type hole， these two factors improve film cooling performance. For radiusing-type hole， the film attach on the wall better and cover wider area. In the region downstream the exit of radiusing-type hole， heat transfer coefficient is high， along the stream wise direction heat transfer coefficient is sharply decreased. The discharge coefficient of radiusing-type hole is 5% higher than cylindrical hole. In general， radiusing-type hole has better flow and heat transfer characteristics.

Key words: Turbine blade；Film cooling；Radiusing-type hole；Experimental study；Numerical simulation

孟通,朱惠人,刘存良,周申平. 边倒圆型气膜孔流动换热特性研究[J]. 推进技术, 2018, 39(5): 1067-1076.

MENG Tong¹,ZHU Hui-ren¹,LIU Cun-liang¹,ZHOU Shen-ping². Experimental and Numerical Study on Film Cooling Performance of Radiusing-Type Hole[J]. Journal of Propulsion Technology, 2018, 39(5): 1067-1076.

参考文献

[1] 葛绍岩, 刘登瀛, 徐靖中, 等. 气膜冷却[M]. 北京:科学出版社, 1985.
[2] Pedersen D R, Eckert E R G, Goldstein R J. Film Cooling with Large Density Differences between the Mainstream and the Secondary Fluid Measured by the Heat-Mass Transfer Analogy[J]. Journal of Heat Transfer, 1977, 99(4): 620-627.
[3] Sinha A K. Film-Cooling Effectiveness Downstream of a Single Row of Holes with Variable Density Ratio[J]. Journal of Turbomachinery, 1991, 113(3): 442-449.
[4] Zaman K. Reduction of Jet Penetration in a Cross-Flow by Using Tabs[R]. AIAA 98-3276.
[5] 杨成凤, 张靖周, 陈利强, 等. 前缘突脊倾斜气膜冷却效果的实验[J]. 工程热物理学报, 2008, 29(7): 1174-1176.
[6] Lu Y, Dhungel A, Ekkad S V. Film Cooling Measurements for Cratered Cylindrical Inclined Holes[R]. ASME GT 2007-27386.
[7] Goldstein R J, Eckert E R G, Burggraf F. Effects of Hole Geometry and Density on Three-Dimensional Film Cooling[J]. International Journal of Heat & Mass Transfer, 1974, 17(5): 595-607.
[8] Hyams D G, Leylek J H. A Detailed Analysis of Film Cooling Physics, Part III: Streamwise Injection with Shaped Holes[J]. Journal of Turbomachinery, 1997, 122(1): 122-132.
[9] Dittmar J, Schulz A, Wittig S. Assessment of Various Film-Cooling Configurations Including Shaped and Compound Angle Holes Based on Large-Scale Experiments[J]. Journal of Turbomachinery, 2003, 125(1): 57-64.
[10] Saumweber C, Schulz A, Wittig S. Free-Stream Turbulence Effects on Film Cooling with Shaped Holes[J]. Journal of Turbomachinery, 2003, 125(1): 65-73.
[11] Gritsch M, Colban W, Scha?R H, et al. Effect of Hole Geometry on the Thermal Performance of Fan-Shaped Film Cooling Holes[J]. Journal of Turbomachinery, 2005, 127(4): 718-725.
[12] Saumweber C, Schulz A. Effect of Geometry Variations on the Cooling Performance of Fan-Shaped Cooling Holes[J]. Journal of Turbomachinery, 2012, 134(6).
[13] Makki Y, Jakubowski G. An Experimental Study of Film Cooling from Diffused Trapezoidal Shaped Holes[R]. AIAA 86-1326
[14] Lee K D, Kim S M, Kim K Y. Numerical Analysis of Film-Cooling Performance and Optimization for a Novel Shaped Film-Cooling Hole[R]. ASME GT 2012-68529.
[15] Issakhanian E, Elkins C J, Eaton J K. Film Cooling Effectiveness Improvements Using a Non-Diffusing Oval Hole[R]. ASME GT 2015-42243.
[16] Sargison J E, Guo S M, Oldfield M L G, et al. A Converging Slot-Hole Film-Cooling Geometry, Part 1: Low-Speed Flat-Plate Heat Transfer and Loss[J]. Journal of Turbomachinery, 2002, 124(3): 453-460.
[17] Sargison J E, Guo S M, Oldfield M L G, et al. A Converging Slot-Hole Film-Cooling Geometry, Part 2: Transonic Nozzle Guide Vane Heat Transfer and Loss[J]. Journal of Turbomachinery, 2002, 124(3): 461-471.
[18] 李广超, 付建, 张魏, 等. 双向扩张孔出口宽度对气膜冷却特性影响[J]. 推进技术, 2016, 37(11):2088-2096. (LI Guang-chao, FU Jian, ZHANG Wei, et al. Effects of Exit Width on Film Cooling Characteristics[J]. Journal of Propulsion Technology, 2016, 37(11): 2088-2096.)
[19] 刘聪, 朱惠人, 付仲议, 等. 涡轮导叶吸力面簸箕型孔气膜冷却特性实验研究[J]. 推进技术, 2016, 37(6): 1142-1150. (LIU Cong, ZHU Hui-ren, FU Zhong-yi, et al. Experimental Study of Film Cooling Characteristics for Dust-Pan Shaped Holes on Suction Side in Turbine Guide Vane[J]. Journal of Propulsion Technology, 2016, 37(6): 1142-1150.)
[20] Bai J T, Zhu H R, Liu C L. Film Cooling Characteristic of Double-Fan-Shaped Film Cooling Holes[R]. ASME GT 2009-59318.
[21] Yang X, Liu Z, Feng Z P. Numerical Evaluation of Novel Shaped Holes for Enhancing Film Cooling Performance[J]. Journal of Heat Transfer, 2015, 137(7), 071701.
[22] 刘存良. 新型高效气膜孔冷却特性研究[D]. 西安:西北工业大学, 2009.
[23] Moffat R J. Describing the Uncertainties in Experimental Results[J]. Experimental Thermal and Fluid Science, 1988, 1(1): 3-17.　　　　　　　　　　　　　*　收稿日期:2017-11-13；修订日期:2018-01-10。基金项目:国家重点基础研究发展计划资助项目(2013CB035702)。作者简介:孟通,男,博士生,研究领域为航空发动机高温部件热防护。E-mail: mengtong1989@163.com通讯作者:朱惠人,男,博士,教授,研究领域为航空发动机高温部件热防护。E-mail: zhuhr@nwpu.edu.cn(编辑:史亚红)