突肩叶尖开槽对叶尖间隙流动和冷却特性的影响

推进技术 ›› 2018, Vol. 39 ›› Issue (1): 125-133.

突肩叶尖开槽对叶尖间隙流动和冷却特性的影响

成锋娜¹,常海萍¹,张镜洋²,田兴江¹,杜治能³

南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学航天学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,中国航空沈阳发动机研究所，辽宁沈阳 110015

发布日期:2021-08-15
作者简介:成锋娜，女，博士生，研究领域为航空发动机高温部件冷却技术。
基金资助:
国家自然科学基金(51406085)；江苏省研究生培养创新工程(KYLX_0306)；中央高校基本科研业务费专项资金。

Effects of Squealer Tip Cutbacks on Tip Leakage Flow and Film-Cooling Characteristics

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Astronautics，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and AECC Shenyang Engine Institute，Shenyang 110015 ，China

Published:2021-08-15

摘要/Abstract

摘要： 为了分析不同叶尖形式下的间隙泄漏流动，采用标准[k-ε]两方程模型求解雷诺平均N-S方程组的数值方法，研究了突肩叶尖开槽对叶尖流动和冷却特性的影响，气膜孔位置、机匣相对运动和吹风比也在考虑范围之内，详细分析了间隙泄漏流场、泄漏流量、泄漏损失以及叶尖气膜冷却效率。研究结果表明:突肩叶尖前缘和尾缘开槽均会使间隙泄漏流量增大，且随着开槽长度的增加而增大。压力侧尾缘开槽会使间隙泄漏损失增大，叶尖气膜冷却效率略微降低；吸力侧尾缘开槽会使得部分泄漏流从开槽处流出间隙，抑制泄漏流与主流之间的掺混，从而减小泄漏损失，并且会使叶尖气膜冷却效率增大；吸力侧前缘开槽对间隙泄漏损失和叶尖气膜冷却效率没有明显影响，但是从前缘进入凹槽内的泄漏流会改变叶尖表面气膜冷却效率的分布。吹风比增大时叶尖结构对叶尖气膜冷却效率的影响减小。机匣相对运动会减小叶尖间隙泄漏流量、泄漏损失和叶尖气膜冷却效率，但是突肩开槽的影响规律不变。

关键词: 突肩开槽；机匣相对运动；吹风比；间隙泄漏损失；气膜冷却效率

Abstract: In order to analyze the leakage flow of different tip configurations， standard two-equation [k-ε] model was adopted to study the effect of squealer tip cutbacks on tip leakage flow and film cooling characteristics by solving the Reynolds-averaged N-S equations. The film hole location， casing relative motion and blowing ratio were also taken into account. The tip leakage flow field， leakage flow rate， leakage loss and tip film-cooling effectiveness were analyzed in detail. The results show that squealer tip leading and trailing edge cutbacks can increase the tip leakage flow rate， which increases with the increase of the cutback length. The pressure side trailing edge cutback will increase the tip leakage loss， but decrease the tip film-cooling effectiveness. The suction side trailing edge cutback will make part of the leakage flow slip out at the cutback location and suppress the mixing between the tip leakage flow and mainstream， then decrease the tip leakage loss. In addition， the tip film-cooling effectiveness at the trailing edge will increase. The addition of the suction side leading edge cutback has tiny influence on the tip leakage loss and tip film-cooling effectiveness， but the leakage flow enter the cavity from the leading edge will change the tip film-cooling effectiveness distribution. The effects of tip geometries on the tip film-cooling effectiveness decrease when the blowing radio increases. The casing relative motion reduces the tip leakage mass flow rate， leakage loss and the tip film-cooling effectiveness， but the effect of the squealer cutbacks is the same.

Key words: Squealer cutback；Casing relative motion；Blowing ratio；Tip leakage loss；Film-cooling effectiveness

成锋娜,常海萍,张镜洋,田兴江,杜治能. 突肩叶尖开槽对叶尖间隙流动和冷却特性的影响[J]. 推进技术, 2018, 39(1): 125-133.

CHENG Feng-na¹,CHANG Hai-ping¹,ZHANG Jing-yang²,TIAN Xing-jiang¹,DU Zhi-neng³. Effects of Squealer Tip Cutbacks on Tip Leakage Flow and Film-Cooling Characteristics[J]. Journal of Propulsion Technology, 2018, 39(1): 125-133.

参考文献

[1] Denton J D. Loss Mechanisms in Turbomachines[R]. ASME 93-GT-435.
[2] Azad G M S, Han J C, Bunker R S, et al. Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer[J]. Journal of Heat Transfer, 2002, 124(3): 452-459.
[3] Azad G M S, Han J C, Boyle R J. Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade [J]. Journal of Turbomachinery, 2000, 122(4): 725-732.
[4] Kwak J S, Han J C. Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade with Single or Double Squealer[J]. Journal of Heat Transfer, 2003, 125(4): 778-787.
[5] Krishnababu S K, Newton P J, Lock G D, et al. Aero-Thermal Investigation of Tip Leakage Flow in Axial Flow Turbines Part I:Effect of Tip Geometry and Tip Clearance Gap[J]. Journal of Turbomachinery, 2007, 131(1): 727-738.
[6] Lee S W, Kim S U. Tip Gap Height Effects on the Aerodynamic Performance of a Cavity Squealer Tip in a Turbine Cascade in Comparison with Plane Tip Results Part 1—Tip Gap Flow Structure[J]. Experiments in Fluids, 2010, 49(4): 1039-1051.
[7] Kwak J S, Han J C. Effects of Rim Location, Rim Height, and Tip Clearance on the Tip and Near Tip Region Heat Transfer of a Gas Turbine Blade[J]. International Journal of Heat and Mass Transfer, 2004, 47(2):5651-5663.
[8] El-Gabry L. Numerical Modeling of Heat Transfer and Pressure Losses for an Uncooled Gas Turbine Blade Tip Effect of Tip Clearance and Tip Geometry[J]. Journal of Thermal Science & Engineering, 2007, 1(2).
[9] Prakash C, Lee C P, Cherry D G, et al. Analysis of Some Improved Blade Tip Concepts[J]. Journal of Turbomachinery, 2006, 128(7): 639-642.
[10] 高杰, 郑群. 叶顶凹槽形态对动叶气动性能的影响[J]. 航空学报, 2013, 34(2): 218-226.
[11] Nasir H, Ekkad S V, Kontrovitz D M, et al. Effect of Tip Gap and Squealer Geometry on Detailed Heat Transfer Measurements Over a High Pressure Turbine Rotor Blade Tip[J]. Journal of Turbomachinery, 2004, 126(2): 221-228.
[12] Mhetras S, Narzary D, Gao Z H, et al. Effect of Cutback Squealer and Cavity Depth on Film-Cooling Effectiveness on a Gas Turbine Blade Tip[J]. Journal of Turbomachinery, 2008, 130(2): 111-120.
[13] Naik S, Georgakis C, Hofer T, et al. Heat Transfer and Film Cooling of Blade Tips and Endwalls[J]. Journal of Turbomachinery, 2012, 134(4): 74-89.
[14] 成锋娜, 常海萍, 张镜洋, 等. 突肩叶尖吸力侧开槽对叶尖间隙流动换热特性的影响[J]. 推进技术, 2016, 37(8): 1543-1550. (CHENG Feng-na, CHANG Hai-ping, ZHANG Jing-yang, et al. Effects of Squealer Tip Suction Side Cutback on Tip Leakage Flow and Heat Transfer Characteristics[J]. Journal of Propulsion Technology, 2016, 37(8): 1543-1550.)
[15] Kwak J S, Han J C. Heat Transfer Coefficients and Film Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade[J]. Journal of Turbomachinery, 2003, 125(4): 648-656.
[16] Mhetras S, Yang H T, Gao Z H, et al. Film-Cooling Effectiveness on Squealer Cavity and Rim Walls of Gas-Turbine Blade Tip[J]. Journal of Propulsion and Power, 2006, 22(4): 889-899.
[17] Yang H T, Chen H C, Han J C. Film-Cooling Prediction on Turbine Blade Tip with Various Film Hole Configurations[J]. Journal of Thermophysics and Heat Transfer, 2006, 20(3): 558-568.
[18] 成锋娜, 常海萍, 张镜洋, 等. 气膜孔位置对突肩叶尖气膜冷却效率的影响 [J]. 航空动力学报, 2017, 32(8): 1844-1852.
[19] Timko L P. Energy Efficient Engine High Pressure Turbine Component Test Performance Report[R]. NASA CR-168289, 1984.
[20] Lee S W, KIM S U. Tip Gap Height Effects on the Aerodynamic Performance of a Cavity Squealer Tip in a Turbine Cascade in Comparison with Plane Tip Results, Part 1: Tip Gap Flow Structure[J]. Experiments in Fluids, 2010, 49(3): 1039-1051.
[21] Zhou C. The Tip Leakage Flow of an Unshrouded High Pressure Turbine Blade with Tip Cooling [J]. Journal of Turbomachinery, 2011, 133(4).
[22] Yang D L, Yu X, Feng Z. Investigation of Leakage Flow and Heat Transfer in a Gas Turbine Blade Tip with Emphasis on the Effect of Rotation[J]. Journal of Turbomachinery, 2010, 132 (4).　　　　　　　　　　　　　*　收稿日期:2016-09-09；修订日期:2016-11-01。基金项目:国家自然科学基金(51406085)；江苏省研究生培养创新工程(KYLX_0306)；中央高校基本科研业务费专项资金。作者简介:成锋娜,女,博士生,研究领域为航空发动机高温部件冷却技术。E-mail: cfn1218@163.com(编辑:张荣莉)