直肋对扩张型尾缘半劈缝气膜冷却特性影响的实验研究

doi:10.13675/j.cnki.tjjs.200325

推进技术 ›› 2020, Vol. 41 ›› Issue (9): 2077-2087.DOI: 10.13675/j.cnki.tjjs.200325

直肋对扩张型尾缘半劈缝气膜冷却特性影响的实验研究

叶林¹，刘存良^1,2，杨寓全¹

1.西北工业大学动力与能源学院，陕西西安 710072;2.西北工业大学陕西省航空动力系统热科学重点实验室，陕西西安 710129

出版日期:2020-09-15 发布日期:2020-09-15
作者简介:叶　林，博士生，研究领域为航空发动机高温部件的强化传热与冷却技术。E-mail：yelin_nwpu@126.com
基金资助:
国家自然科学基金（51776173）；航空动力基金（6141B09050338）；西北工业大学博士论文创新基金（CX201913）。

Experimental Investigation of Effects of Straight Ribs on Film Cooling Performance of Expanded Cutback Surface for Trailing-Edge

1.School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;2.Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System,Northwestern Polytechnical University,Xi’an 710129,China

Online:2020-09-15 Published:2020-09-15

摘要/Abstract

摘要： 为探究布置直肋扰流结构的尾缘半劈缝冷却结构的气膜冷却特性，分别采用压力敏感漆技术和瞬态热色液晶技术研究了直肋对扩张型尾缘半劈缝表面的绝热气膜效率和对流换热系数的影响，详细对比分析了吹风比及直肋宽度对三种不同扩张型半劈缝表面的气膜冷却特性。实验结果表明：直肋的加入对小扩张型半劈缝表面的气膜覆盖产生了不利影响，但仅限在小吹风比工况；而直肋对大扩张型半劈缝表面的气膜覆盖有略小的促进作用，但其绝热气膜效率始终低于小扩张型半劈缝表面。肋宽对半劈缝表面的换热增强大小受半劈缝表面形状影响，随着半劈缝表面扩张程度的增大，宽直肋结构的高换热优势逐渐超越窄直肋结构。直肋型尾缘半劈缝冷却结构可有效提升1.45~2倍的壁面热流密度，小吹风比工况时宜选用带有窄直肋的扩张程度较小的半劈缝表面结构，而大吹风比时宜选用带有宽直肋的扩张程度较大的半劈缝表面结构。

关键词: 涡轮叶片尾缘;扰流半劈缝结构;直肋;压力敏感漆;瞬态热色液晶;气膜冷却

Abstract: To explore the film cooling performance of the cutback trailing-edge with straight-rib turbulence structures, the effects of the straight ribs on the adiabatic film effectiveness and heat transfer coefficient of the expanded cutback surface were studied using the pressure-sensitive paint technology and transient thermochromic liquid-crystal technology, respectively. The effects of the blowing ratio and the rib width on the film cooling performance of the three different expanded cutback surfaces were analyzed and compared in detail. The experimental results show that the addition of straight ribs has an adverse effect on the film coverage on the small expanded cutback surface, but only in the case at low blowing ratio. The straight ribs have a slightly promotion effect on the adiabatic film effectiveness for the large expanded cutback surface, while its adiabatic film effectiveness is always lower than that for the small expanded cutback surface. The heat transfer enhancement of the cutback surface by different rib widths is mainly affected by the shape of the expanded cutback surface. As the expansion of the cutback surface increases, the high heat transfer advantages of the case with wide-ribs gradually surpass the case with narrow-ribs. Compared with the primeval cutback trailing-edge, the wall heat flux of the cutback trailing-edge with straight ribs can significantly improve by a factor of 45%～100%. At the low blowing ratio, it is advisable to choose the case of the small expanded cutback surface with narrow-ribs, while the case of the large expanded cutback surface with wide-ribs should be selected at the high blowing ratio.

Key words: Turbine blade trailing-edge;Turbulated cutback structure;Straight rib;Pressure sensitive paint;Transient thermochromic liquid-crystal;Film cooling

叶林，刘存良，杨寓全. 直肋对扩张型尾缘半劈缝气膜冷却特性影响的实验研究[J]. 推进技术, 2020, 41(9): 2077-2087.

YE Lin¹, LIU Cun-liang^1,2, YANG Yu-quan¹. Experimental Investigation of Effects of Straight Ribs on Film Cooling Performance of Expanded Cutback Surface for Trailing-Edge[J]. Journal of Propulsion Technology, 2020, 41(9): 2077-2087.

参考文献

[1] 朱惠人, 张丽, 郭涛, 等. 高温透平叶片的传热与冷却[M]. 西安: 西安交通大学出版社, 2018.
[2] Han J C, Dutta S, Ekkad S. Gas Turbine Heat Transfer and Cooling Technology[M]. US: CRC Press, Taylor & Francis, 2012.
[3] Cunha F J, Dahmer M T, Chyu M K. Analysis of Airfoil Trailing Edge Heat Transfer and Its Significance in Thermal-Mechanical Design and Durability[J]. Journal of Turbomachinery, 2006, 128(4): 165-176.
[4] Taslim M E, Spring S D, Mehlman B P. Experimental Investigation of Film Cooling Effectiveness for Slots of Various Exit Geometries[J]. Journal of Thermophysics & Heat Transfer, 2015, 6(2): 302-307.
[5] Martini P, Schulz H, Bauer H J. Film Cooling Effectiveness and Heat Transfer on the Trailing Edge Cut-Back of Gas Turbine Airfoils with Various Internal Cooling Designs[J]. Journal of Turbomachinery, 2006, 128(1): 196-205.
[6] Mukherjee D K. Film Cooling with Injection Through Slots[J]. Journal of Engineering for Power, 1976, 98(4): 556-559.
[7] Horbach T, Schulz A, Bauer H J. Trailing Edge Film Cooling of Gas Turbine Airfoils: External Cooling Performance of Various Internal Pin Fin Configurations[J]. Journal of Turbomachinery, 2011, 133(4).
[8] Horbach T, Schulz A, Bauer H J. Trailing Edge Film Cooling of Gas Turbine Airfoils—Effects of Ejection Lip Geometry on Film Cooling Effectiveness and Heat Transfer[J]. Heat Transfer Research, 2010, 41: 849-865.
[9] Choi J. An Experimental Investigation of Turbine Blade Heat Transfer and Turbine Blade Trailing Edge Cooling[D]. US: Texas A&M University, 2004.
[10] 魏建生, 朱惠人, 张丽, 等. 涡轮叶片尾缘劈缝气膜冷却特性实验研究[J]. 工程热物理学报, 2016, 37(9): 1988-1993.
[11] 孙瑞嘉, 杨卫华, 贺宜红, 等. 不同叶片尾缘结构对流换热特性实验[J]. 推进技术, 2011, 32(4): 485-490.
[12] 李廷斌. 不同结构扰流柱对叶片尾缘气膜冷却的影响[D]. 南京: 南京航空航天大学, 2006.
[13] 周志强. 涡轮叶片尾缘半劈缝气膜冷却实验研究[D]. 西安: 西北工业大学, 2005.
[14] Yang Z F, Hu H. An Experimental Investigation on the Trailing Edge Cooling of Turbine Blades[J]. Propulsion and Power Research, 2012, 1(1): 36-47.
[15] Wong T H, Ireland P T, Self K P. Film Cooling Effectiveness Downstream of Trailing Edge Slots Including Cutback Surface Protuberances[J]. International Journal of Turbomachinery, Propulsion and Power, 2016, 1(1).
[16] Krueckels J, Gritsch M, Schneider M. Design Consideration and Validation of Trailing Edge Pressure Side Bleed Cooling[R]. ASME GT 2009-59161.
[17] Taslim M E, Wadsworth C M. An Experiment Investigation of the Rib Surface-Averaged Heat Transfer Coefficient in a Rib-Roughed Square Passages[J]. Journal of Turbomachinery, 1997, 119(2): 381-389.
[18] Chen D W, Zhu H R, Liu C L, et al. Combined Effects of Unsteady Wake and Free-Stream Turbulence on Turbine Blade Film Cooling with Laid-Back Fan-Shaped Holes Using PSP Technique[J]. International Journal of Heat and Mass Transfer, 2019, 133: 382-392.
[19] 刘存良, 朱惠人, 白江涛. 收缩-扩张形气膜孔提高气膜冷却效率的机理研究[J]. 航空动力学报, 2008, 23(4): 512-517.
[20] Ye L, Liu C L, Zhou D E, et al. Experimental and Numerical Investigations on the Heat Transfer of Film Cooling with Cylindrical Holes Fed with Internal Coolant Cross Flows[J]. Journal of Heat Transfer, 2020, 142(5).
[21] Ye L, Liu C L, Zhu H R, et al. Experimental Investigations on the Effect of Cross-Flow Reynolds Number on Film Cooling Effectiveness[J]. AIAA Journal, 2019, 57(11): 4804-4818.
[22] 白江涛, 朱惠人, 刘存良. 双参数传热实验的液晶瞬态测量不确定度分析[J]. 航空动力学报, 2009, 24(9): 1945-1951.
[23] Holloway D S, Leylek J H, Buck F A. Pressure Side Bleed Film Cooling Part2—Unsteady Framework for Experimental and Computational Results[R]. ASME GT 2002-30472.
[24] Murata A, Yano K, Hanai M, et al. Arrangement Effects of Inclined Teardrop-Shaped Dimples on Film Cooling Performance of Dimpled Cutback Surface at Airfoil Trailing Edge[J]. International Journal of Heat and Mass Transfer, 2017, 107: 761-770.
[25] Murata A, Nishida S, Saito H, et al. Effects of Surface Geometry on Film Cooling Performance at Airfoil Trailing Edge[R]. ASME GT 2011-45355.
[26] 刘松龄, 陶智. 燃气涡轮发动机的传热和空气系统[M]. 上海: 上海交通大学出版社, 2017.

直肋对扩张型尾缘半劈缝气膜冷却特性影响的实验研究

Experimental Investigation of Effects of Straight Ribs on Film Cooling Performance of Expanded Cutback Surface for Trailing-Edge

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