利用W型槽提高气膜冷却效率机理

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 520-526.

利用W型槽提高气膜冷却效率机理

李广超¹,陈钰恺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,中国航空工业集团公司沈阳发动机设计研究所，辽宁沈阳 110015,中国航空工业集团公司沈阳发动机设计研究所，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(51306126；51406124)；航空科学基金(2012ZB54006)；辽宁省自然科学基金(2015020112)。

Mechanism on Increasing Film Cooling Effectiveness

Liao Ning Key Laboratory of Advanced Test and Measurement Technique for Aerospace Propulsion System， Faculty of Aerospace Engineering，Shenyang Aerospace University，Shenyang 110136，China,Liao Ning Key Laboratory of Advanced Test and Measurement Technique for Aerospace Propulsion System， Faculty of Aerospace Engineering，Shenyang Aerospace University，Shenyang 110136，China,Shenyang Aeroengine Research Institute，Aviation Industry Corporation of China，Shenyang 110015，China,Shenyang Aeroengine Research Institute，Aviation Industry Corporation of China，Shenyang 110015，China and Liao Ning Key Laboratory 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： 为了探讨圆柱孔出口开有W型槽结构的气膜冷却机理，数值模拟研究了W型槽与横向槽下游流场、温度场及气膜冷却效率。分析了W型槽深度对气膜冷却效率的影响。结果表明:相比于横向槽，W型槽结构展向平均气膜冷却效率提高70%～130%。随着W型槽深度增加，气膜孔出口下游的对漩涡减弱，两侧的附加漩涡增强，最终形成一对反向对漩涡。小吹风比0.5时，三种W型槽深结构的展向平均气膜冷却效率差别小于8%；大吹风比1.5时，槽深0.5D(D为气膜孔孔径)结构展向平均气膜冷却效率高于槽深0.25D结构的展向平均气膜冷却效率75%～150%。槽深0.5D和0.75D结构的展向平均气膜冷却效率基本相同，差别小于3%。

关键词: 涡轮叶片；薄膜冷却；冷却效率；涡对；W型槽

Abstract: In order to explore the film cooling performance of cylindrical holes attached with W shape slots，the flow field，the temperature field and the film cooling effectiveness distribution on the downstream wall of W shape slots and transverse slots were studied by numerical simulation. Influences of the depths of the W shape slot on the film cooling effectiveness were analyzed. The results show that the spanwise averaged film cooling effectiveness of the W shape slot model increased by 70%～130% compared with that of the transverse slot. With the increase of W shape slot depths，the rotating vortices are weakened in the downstream of the film cooling hole exit，and the additional vortices are strengthened in the downstream of both sides of the hole，eventually forming a pair of reverse counter-rotating vortices. At the low blowing ratio of 0.5，the difference of the spanwise averaged film cooling effectiveness is less than 8% among the three depths of W-shape slots. At the high blowing ratio of 1.5，the spanwise averaged film cooling effectiveness of the slot depth 0.5D (D means film hole diameter)case is much higher than that of 0.25D by 75%～150%. However，the spanwise averaged film cooling effectiveness of the slot depth of 0.5D case is close to 0.75D case，in which the difference is less than 3%.

Key words: Turbine blades；Film cooling；Cooling effectiveness；Vortex pair；W-shape slot

李广超,陈钰恺,刘永泉,杜治能,张魏. 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-chao¹,CHEN Yu-kai¹,LIU Yong-quan²,DU Zhi-neng²,ZHANG Wei¹. Mechanism on Increasing Film Cooling Effectiveness[J]. Journal of Propulsion Technology, 2016, 37(3): 520-526.

参考文献

[1] Yuen C H N, Martinez-Botas R F. Film Cooling Charcateristics of a Single Round Hole at Various Streamwise Angle in a Crossflow Part I :Effectiveness[J]. Heat and Mass Transfer, 2003, 46(2): 221-235.
[2] 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.
[3] 朱惠人, 许都纯, 刘松龄, 等. 簸箕形气膜孔气膜冷却实验研究[J]. 航空学报, 1997, 18(5): 535-539.
[4] 朱惠人, 许都纯, 刘松龄. 气膜孔形状对孔排下游冷却效率的影响[J]. 航空学报, 2002, 23(1): 75-78.
[5] Yoji Okita, Masakazu Nishiura. Film Effectiveness Performance of an Arrowhead-Shaped Film-Cooling Hole Geometry[R]. ASME GT 2006-90108.
[6] 何立明, 蒋永健, 康强, 等. 利用上游斜坡改善气膜冷却效率的数值研究[J]. 推进技术, 2009, 30(1): 9-13. (HE Li-ming, JIANG Yong-jian, KANG Qiang, et al. Numerical Investigation on Improving Film Cooling Effectiveness with an Upstream Ramp[J]. Journal of Propulsion Technology, 2009, 30(1): 9-13.)
[7] Fric T F, Campbell R P. Method for Improving the Cooling Effectiveness of a Gaseous Coolant Stream Which Flows through a Substrate and Related Articles of Manufacture[P]. US: 6234755 , 2002-05-22.
[8] Prasad Kalghatgi, Sumanta Acharya. Improved Film Cooling Effectiveness with a Round Film Cooling Hole Embedded in a Contoured Crater[R]. ASME GT 2014-26600.
[9] 于锦禄, 赵罡, 何立明. 横向槽横向宽度对气膜孔冷却性能影响的数值研究[J]. 中国电机工程学报, 2010, 15(1): 79-84.
[10] Bunker R S. Film Cooling Effectiveness Due to Discrete Holes with in a Transverse Surface Slot[R]. ASME GT 2002-30178.
[11] 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.)
[12] Lu Y P, NasirH, Ekkad S V. Film Cooling from a Row of Holes Embedded in Transverse Slots[R]. ASME GT 2005-68598.
[13] Lu Y P, Ekkead S V. Predictions of Film Cooling from Cylindrical Holes Embedded in Trenches[R]. AIAA 2006-3401. 　　　　　　　　　　　　　　　　 .
[14] Waye Scot K, Bogard David G. High-Resolution Film Cooling Effectiveness Measurement of Axial Holes Embedded in a Transverse Trench with Various Trench Configurations[R]. ASME GT 2006-90266.
[15] 章大海, 陈秋炀, 曾敏. 不同横槽结构对气膜冷却效率影响的数值研究[J]. 航空动力学报, 2008, 23(4): 611-616.
[16] 蒋永健, 何立明, 于锦禄, 等. 利用横向槽改善气膜冷却效率的数值研究[J]. 推进技术, 2008, 29(3):286-289. (JIANG Yong jian, HE Li-ming, YU Jin lu, et al. Numerical Investigation on Improving Film Cooling Effectiveness with Transverse Slots[J]. Journal of Propulsion Technology, 2008, 29(3): 286-289.)
[17] Wang T, Chin talapati S, Bunker R S, et al. Jet Mixing in a Slot [J]. Experimental Thermal and Fluid Science, 2000, 22(1): 1-17.
[18] Alok Dhungel, Yiping Lu, Wynn Phillips. Film Cooling from a Row of Holes Supplemented with Antivortex Holes[J]. ASME Journal of Turbomachinery, 2009, 131 (4): 1-10.
[19] 廖高良, 王新军, 李军. 带槽双射流气膜冷却数值研究[J]. 西安交通大学学报, 2014, 48(3): 34-38.
[20] Kusterer K, Bohn D, Sugimoto T. Double Jet Ejection of Cooling Air for Improved Film Cooling [J]. ASME Journal of Turbomachinery, 2007, 129(10): 809-815.
[21] 李广超, 吴冬, 张魏, 等. 次孔方位角对单入口-双出口孔射流气膜冷却效率影响[J]. 航空动力学报, 2011, 26(7): 1598-1604.
[22] 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): 598-604.
[23] Kusterer K, Elyas A, Bohn D, et al. Aparametric Study on the Influence of the Lateral Ejection Angle of Double-Jet Holes on the Film Cooling Effectiveness for High Blowing Ratios[R]. ASME GT 2009-59321.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2015-03-11；修订日期:2015-04-27。基金项目:国家自然科学基金(51306126；51406124)；航空科学基金(2012ZB54006)；辽宁省自然科学基金(2015020112)。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