凹槽状叶顶涡轮叶片传热特性的数值研究

推进技术 ›› 2014, Vol. 35 ›› Issue (5): 618-623.

凹槽状叶顶涡轮叶片传热特性的数值研究

杜昆,宋立明,李军

西安交通大学能源与动力工程学院，陕西西安 710049;西安交通大学能源与动力工程学院，陕西西安 710049;西安交通大学能源与动力工程学院，陕西西安 710049

发布日期:2021-08-15
作者简介:杜昆(1990—)，男，硕士生，研究领域为叶片流固耦合和多学科优化设计。E-mail :dk_703301@stu.xjtu.edu.cn
基金资助:
国家自然科学基金项目(51106123)；教育部博士点基金资助项目(20100201120010)。

Numerical Investigations on Heat Transfer Characteristics of Turbine Blade with Squealer Tip

School of Energy and Power Engineering，Xi ’ an Jiaotong University，Xi ’ an 710049，China;School of Energy and Power Engineering，Xi ’ an Jiaotong University，Xi ’ an 710049，China;School of Energy and Power Engineering，Xi ’ an Jiaotong University，Xi ’ an 710049，China

Published:2021-08-15

摘要/Abstract

摘要： 采用计算流体动力学软件ANSYS-CFX数值求解三维Reynolds-Averaged Navier-Stokes(RANS)和标准 k - ω 紊流模型研究了涡轮叶片凹槽状叶顶的传热特性。数值预测的平顶部叶顶的换热系数分布与实验数据吻合良好，验证了数值方法的可靠性。计算分析了凹槽深度和肩壁厚度对凹槽状叶顶传热特性的影响，还分析了动叶与机匣相对运动下的凹槽状叶顶无气膜冷却和中弧线布置气膜冷却时的流动换热特性。研究结果表明:在肩壁厚度一定时随着凹槽深度的增加叶顶换热系数降低；在1%叶高的叶顶间隙和2%叶高的凹槽深度及4种肩壁条件下1.0mm肩壁厚度时叶顶换热系数最小。相比于动叶与机匣均静止时，动叶和机匣之间的相对运动能够增强动叶顶部的换热效果；动叶与机匣间的相对运动能够增强前缘处气膜冷却效果，总体来说动叶旋转时的离心力和哥氏力对凹槽状叶顶的气膜冷却效果影响有限。

关键词: 涡轮叶片；凹槽状叶顶；气膜冷却；传热；数值模拟

Abstract: Numerical investigations on the heat transfer characteristics of the turbine blade with squealer tip was carried out using three-dimensional Reynolds-Averaged Navier-Stokes(RANS)and standard k - ω turbulent model based on the CFD software ANSYS-CFX. The numerical results agree well with the experimental data for the turbine blade with flat tip. The accuracy of the utilized numerical approach was demonstrated. Effects of squealer depth and squealer rim width on the heat transfer performance of turbine blade with squealer tip and effects of the relative motion between the blade and casing on the heat transfer characteristics of the squealer tip with film holes located at the camber line on the squealer tip and without film cooling structure were conducted. The numerical results show that the heat transfer coefficient of the blade tip decreases with the increase of the squealer depth at the fixed rim width. The minimization of the averaged heat transfer coefficients of the tip was obtained at the tip clearance with 1% span and squealer depth with 2% span and rim width with 1.0mm among 4 cases. The relative motion between the blade and casing can strengthen the heat transfer performance by comparison of the rotor and casing stationary case. The relative motion between the rotor blade and casing can only strengthen the film cooling performance near the leading edge. The effects of the centrifugal force and Coriolis force on the film cooling performance of squealer tip in total are limited.

Key words: Turbine blade； Squealer tip；Film cooling；Heat transfer；Numerical simulation

杜昆,宋立明,李军. 凹槽状叶顶涡轮叶片传热特性的数值研究[J]. 推进技术, 2014, 35(5): 618-623.

DU Kun,Song Li-ming,LI Jun. Numerical Investigations on Heat Transfer Characteristics of Turbine Blade with Squealer Tip[J]. Journal of Propulsion Technology, 2014, 35(5): 618-623.

参考文献

[1] 刘大响. 高性能航空发动机的发展对材料技术的要求[J]. 燃气涡轮试验与研究， 1998， 11(3): 125.
[2] 韩介勤. 燃气轮机冷却和传热技术[M]. 西安: 西安交通大学出版社， 2005.
[3] Bogard D G， Thole K A. Gas Turbine Film Cooling[J]. Journal of Propulsion and Power ， 2006， 22(2): 249-270.
[4] Bunker R S. Axial Turbine Blade Tips: Function， Design， and Durability[J]. Journal of Propulsion and Power ， 2006， 22(2): 271-285.
[5] Azad G S， Han J C， Teng Shuye， et al. Heat Transfer and Pressure Distributions on a Gas Turbine Blade tip[J]. ASME Journal of Turbomachinery ， 2000， 122(4):717-724.
[6] Azad G S， Han J C， Boyle R J. Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade[J]. ASME Journal of Turbomachinery ， 2000， 122(4): 725-732.
[7] Kwak J S， Han J C， Heat Transfer Coefficient on a Gas Turbine Blade Tip and Near Tip Regions[R]. AIAA 2002-3012.
[8] Naik S， Georgakis C， Lengani D. Heat Transfer and Film Cooling of Blade Tips and Endwalls[J]. ASME Journal of Turbomachinery ， 2012， 134(4).
[9] Yang D， Yu X， Feng Z. Investigation of Leakage Flow and Heat Transfer in a Gas Turbine Blade With Emphasis on the Effect of Rotation[J]. ASME Journal of Turbomachinery ， 2010， 132(4).
[10] Tallman J A. A Computational Study of Tip Desensitization in axial Flow Turbines[D]. Pennsylvania: The Pennsylvania State University ， 2005.
[11] Zhou C， Hodson H， Tibbott I， et al. Effects of Endwall Motion on the Aero-Thermal Performance of a Winglet Tip in a HP Turbine[J]. ASME Journal of Turbomachinery ， 2012， 134(6).
[12] 李广超，朱慧人，白江涛，等. 气膜孔布局对前缘气膜冷却效率影响的实验[J]. 推进技术， 2008， 29(2): 153-157.(LI Guang-chao， ZHU Hui-ren， BAI Jiang-tao， et al. Experimental Investigation of Film Cooling Effectiveness on Leading Edge with Various Geometries [J]. Journal of Propulsion Technology ， 2008， 29(2): 153-157.)
[13] 李军，王金山，蒋勇，等. 凹槽状动叶顶部非定常气膜冷却性能的研究[J]. 西安交通大学学报， 2010， 44(5): 5-10.
[14] 虞跨海，杨茜，岳珠峰. 高压涡轮冷却叶片叶顶结构气动与传热[J]. 推进技术， 2012， 33(2): 174-178. (YU Kuahai， YANG Xi， YUE Zhufeng. Aerodynamic and Heat Transfer of Cooling Blade Tips for High Pressure Turbine [J]. Journal of Propulsion Technology ， 2012， 33(2):174-178. )
[15] 贾惟，刘火星. 涡轮叶栅叶冠泄漏流动数值研究[J]. 推进技术， 2013， 34(3): 316-325.(JIA Wei， LIU Huo-xing. Numerical Investigation on Shroud Leakage Flow in Turbine Cascade[J]. Journal of Propulsion Technology ， 2013， 34(3): 316-325.)