圆孔-半椭圆槽组合结构气膜冷却机理

推进技术 ›› 2018, Vol. 39 ›› Issue (3): 605-611.

圆孔-半椭圆槽组合结构气膜冷却机理

李广超¹,周帅¹,刘永泉²,杜治能²,张魏¹

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，辽宁沈阳 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，辽宁沈阳 110136,中国航发沈阳发动机研究所，辽宁沈阳 110015,中国航发沈阳发动机研究所，辽宁沈阳 110015,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，辽宁沈阳 110136

发布日期:2021-08-15
作者简介:李广超，男，博士，副教授，研究领域为航空发动机热端部件传热冷却。
基金资助:
国家自然科学基金(51406124)；辽宁省自然科学基金(201602576)。

Mechanism of Film Cooling for Combined Cylindrical Holes and Semi-Elliptical Slots

Liao Ning Key Lab of Advanced Test and Measurement Technique for Aerospace Propulsion System， Faculty of Aerospace Engineering，Shenyang Aerospace University，Shenyang 110136，China,Liao Ning Key Lab of Advanced Test and Measurement Technique for Aerospace Propulsion System， Faculty of Aerospace Engineering，Shenyang Aerospace University，Shenyang 110136，China,AECC Shenyang Engine Institute，Shenyang 110015，China,AECC Shenyang Engine Institute，Shenyang 110015，China and Liao Ning Key Lab of Advanced Test and Measurement Technique for Aerospace Propulsion System， Faculty of Aerospace Engineering，Shenyang Aerospace University，Shenyang 110136，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探讨半椭圆槽改善圆孔射流气膜冷却机理，数值模拟研究了圆孔-半椭圆型槽组合结构下游流场、温度场及气膜冷却效率。分析了不同吹风比下半椭圆槽深度对气膜冷却特性的影响。结果表明:吹风比0.5和1.5时，和锯齿槽相比，半椭圆槽更容易形成反向对漩涡，展向平均气膜冷却效率提高5%～119%。随着半椭圆槽深度的增加，孔间区域的气膜冷却效率提高，展向气膜冷却效率分布更均匀。吹风比0.5时，槽深度对半椭圆槽展向平均气膜冷却效率的影响很小，三种槽深的差距在15%以内。吹风比1.5时，半椭圆槽深度为0.5倍孔径的展向平均气膜冷却效率最佳，分别比槽深度为0.25倍和0.75倍孔径的半椭圆槽高55%～107%和2%～16%。

关键词: 气膜冷却；半椭圆槽；涡轮叶片；冷却效率；对漩涡

Abstract: Numerical simulation was carried out to study the flow field， temperature field and film cooling effectiveness downstream of cylindrical holes with semi-elliptical shape slots to reveal the mechanism of film cooling combined cylindrical holes and semi-elliptical slots. Influences of the depths of the semi-elliptical shape slots on film cooling were analyzed at different blowing ratios. The results show that the semi-elliptical slots are more easily to form counter-rotating vortices and the spanwise averaged film cooling effectiveness of the semi-elliptical slot model increased 5%～119% compared with that of the saw tooth slot when the blowing ratio is 0.5 and 1.5. The distribution of spanwise film cooling effectiveness is more uniform and film cooling effectiveness is improved in the span regions between the cylindrical holes as the increase of the depths of semi-elliptical slot. At the blowing ratio of 0.5， the influence of the depths of the semi-elliptical shape slots on spanwise averaged film cooling is less than 15%. At the blowing ratio of 1.5， the spanwise averaged film cooling effectiveness of the semi-elliptical slot depths of 0.5 times of film hole diameter case is higher than that of 0.25 and 0.75 times of film hole diameter by 55%～107% and 2%～16%， respectively.

Key words: Film cooling；Semi-elliptical slot；Turbine blade；Cooling effectiveness；Vortex pair

李广超,周帅,刘永泉,杜治能,张魏. 圆孔-半椭圆槽组合结构气膜冷却机理[J]. 推进技术, 2018, 39(3): 605-611.

LI Guang-chao¹,ZHOU Shuai¹,LIU Yong-quan²,DU Zhi-neng²,ZHANG Wei¹. Mechanism of Film Cooling for Combined Cylindrical Holes and Semi-Elliptical Slots[J]. Journal of Propulsion Technology, 2018, 39(3): 605-611.

参考文献

[1] 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 and Mass Transfer, 1974, 17(5): 595-607.
[2] 廖乃冰, 朱惠人, 李广超, 等. 双扇形孔气膜冷却效率的研究[J]. 航空动力学报, 2008, 23(11): 2082-2087.
[3] 徐红洲, 刘松龄, 许都纯. 扇形和圆形气膜冷却孔的流动和传热实验比较[J]. 航空动力学报, 1997, 12(1): 51-55.
[4] Dai P, Lin F. Numerical Study on Film Cooling Effectiveness from Shaped and Crescent Holes[J]. Heat Mass Transfer, 2011, 47(2): 147-154.
[5] Bunker R S. A Review of Shaped Hole Turbine Film- Cooling Technology[J]. Journal of Heat Transfer, 2005, 127(4): 441-453.
[6] LeBlanc C, Narzary D P, Ekkad S. Film-Cooling Performance of Antivortex Hole on a Flat Plate[J]. Journal of Turbomachinery, 2013, 135(6).
[7] 李广超, 柏树生, 吴冬, 等. 气膜孔形状对涡轮叶片气膜冷却影响的研究进展[J]. 热能动力工程, 2010, 25(6): 581-585.
[8] Kusterer K, Bohn D, Sugimoto T, et al. Double-Jet Ejection of Cooling Air for Improved Film Cooling[J]. Journal of Turbomachinery, 2007, 129(10): 809-815.
[9] 张玲, 郭瑞红, 郭达飞, 等. 姊妹孔平板气膜冷却效率的数值模拟[J]. 动力工程学报, 2014, 34(9): 696-700.
[10] 吴宏, 杨庆. 抑涡孔气膜冷却的大涡模拟[J]. 航空动力学报, 2012, 27(12): 2648-2654.
[11] Heidmann J D, Ekkad S. A Novel Antivortex Turbine Film-Cooling Hole Concept[J]. Journal of Turbomachinery, 2008, 130(3).
[12] Zhou W, Hu H. Improvements of Film Cooling Effectiveness by Using Barchan Dune Shaped Ramps[J]. International Journal of Heat and Mass Transfer, 2016, 103(4): 443-456.
[13] Na S, Shih T I P. Increasing Adiabatic Film-Cooling Effectiveness by Using an Upstream Ramp[J]. Journal of Heat Transfer, 2007, 129(4): 464-471.
[14] 戴萍, 林枫. 横向槽结构对气膜冷却效果影响的数值研究[J]. 推进技术, 2011, 32(2): 253-260. (DAI Ping, LIN Feng. Numerical Investigation on the Influence of Transverse Slot Configurations on Film Cooling Effect[J]. Journal of Propulsion Technology, 2011, 32(2): 253-260.)
[15] 张玲, 王冲. 不同横斜槽结构对气膜冷却效果影响的正交模拟[J]. 推进技术, 2016, 37(5): 922-929. (ZHANG Ling, WANG Chong. Orthogonal Simulation of Effects of Different Transverse Declining Slot Structures on Film Cooling[J]. Journal of Propulsion Technology, 2016, 37(5): 922-929.)
[16] Waye S K, Bogard D G. High-Resolution Film Cooling Effectiveness Measurements of Axial Holes Embedded in a Transverse Trench with Various Trench Configurations[J]. Journal of Turbomachinery, 2007, 129(2): 294-302.
[17] Lu Y, Nasir H, Ekkad S V. Film Cooling from a Row of Holes Embedded in Transverse Slots[R]. ASME GT 2005-68598.
[18] Baheri S, Tabrizi S P A, Jubran B A. Film Cooling Effectiveness from Trenched Shaped and Compound Holes[J]. Heat and Mass Transfer, 2008, 44(8): 989-998.
[19] An B T, Liu J J, Zhang X D, et al. Film Cooling Effectiveness Measurements of a Near Surface Streamwise Diffusion Hole[J]. International Journal of Heat and Mass Transfer, 2016, 103(1): 1-13.
[20] 李广超, 陈钰恺, 刘永泉, 等. 利用W型槽提高气膜冷却效率机理[J]. 推进技术, 2016, 37(3): 520-526. (LI Guang-chao, CHEN Yu-kai, LIU Yong-quan, et al. Mechanism on Increasing Film Cooling Effectiveness by W Shape Slots[J]. Journal of Propulsion Technology, 2016, 37(3): 520-526.)　　　　　　　　　　　　　*　收稿日期:2016-10-25；修订日期:2016-12-09。基金项目:国家自然科学基金(51406124)；辽宁省自然科学基金(201602576)。作者简介:李广超,男,博士,副教授,研究领域为航空发动机热端部件传热冷却。E-mail: ligc706@163.com(编辑:史亚红)