基于弯曲叶片的燃气涡轮导叶数值研究

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 443-448.

基于弯曲叶片的燃气涡轮导叶数值研究

张晓辉¹,陈绍文²,李燕飞²

航天科工海鹰集团有限公司，北京 100074,哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:张晓辉，男，硕士，工程师，研究领域为叶轮机械流动控制及气动分析。
基金资助:
国家自然科学基金(51206035)；国家自然科学基金创新研究群体项目(51121004)。

Numerical Investigation for Curved Guide Vane in Gas Turbine

HIWING Group of CASIC Co.Ltd.，Beijing 100074，China,Energy Science and Engineering School，Harbin Institute of Technology，Harbin 150001，China and Energy Science and Engineering School，Harbin Institute of Technology，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 采用三维数值方法，对小展弦比、考虑冷却的燃气涡轮弯曲导叶进行了三维流场模拟，通过对比分析不同的叶片弯曲方案，以探讨叶片弯曲控制二次流动、减小损失的机理。结果表明，由于导叶的径向二次流影响范围较小，正弯设计对叶栅气动性能的改善效果优于反弯；正弯设计能有效降低上端区的损失，最大降幅接近5%，而正弯和反弯设计都对下端区流动和损失影响较小。采用正弯设计后叶片吸力面的冷却效果变化不大，但显著降低了压力面的冷却效果，使得高温区域增加。

关键词: 燃气涡轮；弯曲叶片；二次流；气动性能；数值研究

Abstract: A low aspect ratio and curved turbine guide vane with cooling was investigated by 3-D numerical simulation. Through a comparative analysis of schemes with various bowing laws，the mechanism of controlling secondary flow and reducing losses was explored and discussed. The results show that as a result of a smaller range of radial secondary flow，a positively curved blade can improve aerodynamic performance of the cascade，which has a more effect than that of a negatively curved blade. A blade making use of positive curved design could effectively reduce the loss of the upper end-wall and the maximum amplitude of the loss reduction among different schemes reaches 5%. Positive and negative curved designs have little impact on the flow and loss of the lower endwall. When the positive curved design is put into use，the cooling effect of suction surface of the blade does not change a lot. However，the positive design significantly lowers the cooling performance of pressure side and this leads to a rise of high-temperature area.

Key words: Gas turbine；Curved blade；Secondary flow；Aerodynamic performance；Numerical investigation

张晓辉,陈绍文,李燕飞. 基于弯曲叶片的燃气涡轮导叶数值研究[J]. 推进技术, 2016, 37(3): 443-448.

ZHANG Xiao-hui¹,CHEN Shao-wen²,LI Yan-fei². Numerical Investigation for Curved Guide Vane in Gas Turbine[J]. Journal of Propulsion Technology, 2016, 37(3): 443-448.

参考文献

[1] Denton J D. The 1993 IGTI Scholar Lecture: Loss Mechanisms in Turbomachines[J]. Journal of Turbomachinery,1993,115(4): 621-656.
[2] 赵磊, 乔渭阳, 谭洪川. 弯曲/倾斜叶片对大展弦比涡轮气动性能影响[J]. 推进技术, 2011, 32(5): 625-630. (ZHAO Lei, QIAO Wei-yang, TAN Hong-chuan. Effects of Bowed/Lean Vanes on Aerodynamic Performance of High Aspect Ratio Turbine[J]. Journal of Propulsion Technology, 2011, 32(5): 625-630.)
[3] Tan C, Zhang H, Chen H, et al. Blade Bowing Effect on Aerodynamic Performance of a Highly Loaded Turbine Cascade[J]. Journal of Propulsion and Power, 2010, 26(3): 604-608.
[4] HAN W J, WANG Z Q, TAN C Q, et al. Effects of Leaning and Curving of Blades with High Turning Angles on the Aerodynamic Characteristics of Turbine Rectangular Cascades[J]. Journal of Turbomachinery, 1994, 116(3): 417-424.
[5] Schobeiri M T, Suryanarayanan A, Jermann C, et al. A Comparative Aerodynamic and Performance Study of a Three-Stage High Pressure Turbine with 3-D Bowed Blades and Cylindrical Blades[R]. ASME 2004-GT-53650.
[6] 王雷, 胡松岩. 动力涡轮弯扭导向叶片的设计[J]. 航空发动机, 2001 (4): 6-10.
[7] Kobayashi K, Honjo M, Tashiro H, et al. Verification of Flow Pattern for Three-Dimensional-Designed Blades[R]. IMechE Paper C, 1991, 423.
[8] 颜培刚, 王松涛, 冯国泰. 叶片弯曲对气冷涡轮叶栅气动性能影响的数值研究[J]. 航空动力学报, 2006, 21(2): 261-267.
[9] 陈浮, 杨科, 宋彦萍, 等. 大转角反弯叶栅气膜冷却实验研究[J]. 航空动力学报, 2004, 19(2): 219-223.
[10] Rajendran V P, Sajben M, Dimcco R. Experimental Investigation of Aerodynamics of Turbine Blade Trailing Edge Cooling at Transonic Speeds[R]. AIAA 2000-3640.
[11] Hoda A, Acharya S. Prediction of a Film Coolant Jet in Crossflow with Different Turbulence Models[J]. Journal of Turbomachinery, 2000, 122(3): 558-738.
[12] Friedrichs S, Hodson H P, Dawes W N. Aerodynamics Aspects of Endwall Film Cooling[J]. Journal of Turbomachinery, 1997, 119(3): 786-793.
[13] 高丽敏, 刘波, 姜正礼, 等. 不同尾缘喷射对涡轮叶栅气动性能的影响[J]. 推进技术, 2000, 21(2): 33-36. (GAO Li-min, LIU Bo, JIANG Zheng-li, et al. Aerodynamic Effect of Trailing Edge Coolant Ejection on Transonic Turbine Cascade[J]. Journal of Propulsion Technology, 2000, 21(2): 33～36.)
[14] 乔渭阳, 曾军, 曾文演, 等. 气膜孔喷气对涡轮气动性能影响的实验研究[J]. 推进技术, 2007, 28(1): 14-19. (QIAO Wei-yang, ZENG Jun, ZENG Wen-yan, et al. Experimental Studies for the Aerodynamic Loss in Gas Turbine with Film Cooling[J]. Journal of Propulsion Technology, 2007, 28(1): 14～19.)
[15] 罗磊. 小流量涡轴发动机涡轮气动及冷却技术研究[D] . 哈尔滨:哈尔滨工业大学, 2012.　　　　　　　　　　　　　*　收稿日期:2014-10-27；修订日期:2015-01-05。基金项目:国家自然科学基金(51206035)；国家自然科学基金创新研究群体项目(51121004)。作者简介:张晓辉,男,硕士,工程师,研究领域为叶轮机械流动控制及气动分析。E-mail: zhangxiaohui_hit@163.com(编辑:史亚红)