不同换算转速对高负荷风扇静子角区流动的影响

推进技术 ›› 2017, Vol. 38 ›› Issue (10): 2348-2357.

不同换算转速对高负荷风扇静子角区流动的影响

何成¹,王如根¹,李仁康¹,宋昊林¹,何畏²,谢祥勇³

空军工程大学工程学院，陕西西安 710038,空军工程大学工程学院，陕西西安 710038,空军工程大学工程学院，陕西西安 710038,空军工程大学工程学院，陕西西安 710038,中国人民解放军95503部队，贵州遵义 563127,中国人民解放军94855部队，浙江衢州 324000

发布日期:2021-08-15
作者简介:何成，男，硕士生，研究领域为推进系统气动热力理论与工程。

Effects on High-Load Fan’s Flow Structure in Stator Corner under Different Corrected Rotation Speeds

Engineering College，Air Force Engineering University，Xi’an 710038，China,Engineering College，Air Force Engineering University，Xi’an 710038，China,Engineering College，Air Force Engineering University，Xi’an 710038，China,Engineering College，Air Force Engineering University，Xi’an 710038，China,95503 Troop of Chinese People’s Liberation Army，Zunyi 563127，China and 94855 Troop of Chinese People’s Liberation Army，Quzhou 324000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探究影响高负荷风扇的失稳机制，对风扇第二级静子叶根角区气流分离的形成原因进行了研究，分析了不同换算转速对角区的流动状态以及壁角涡形成与发展的影响。研究表明，经过静子叶根前缘的气流逐渐发展形成了壁角涡，而壁角涡的存在促使了静子吸力面角区的气流分离，且随着风扇工况向近失速点移动，更多的角区气流直接参与了壁角涡的形成。在所研究的范围内，换算转速增加会导致壁角涡强度增加、影响范围扩大；在95% ~ 105%换算转速，壁角涡是引起角区气流分离的主要因素，而在85%换算转速，壁角涡已不再是引起角区气流分离和风扇失稳的主要原因。

关键词: 高负荷风扇；角区流动分离；壁角涡；换算转速

Abstract: In order to explore the instability mechanism of a high-load fan， the formation of the corner flow separation of the second stator in the two-stage fan was studied. The flow structure in corner and the development of corner vortex at different corrected rotation speed were analyzed. The results show that corner vortex is formed by the flow which pass the leading edge of stator root， and the corner vortex promote the corner flow separation of the second stator. While the fan condition is near stall， more flow in corner is involved in the formation of corner vortex. In the limits of the study， the increase of corrected rotation speed lead to the stronger corner vortex and its wider influence area. Corner vortex is the main reason of the corner flow separation at 95% ~ 105% corrected rotation speed， while corner vortex is not the major reason of the corner flow separation and fan instability at 85% corrected rotation speed.

Key words: High-load compressor；Corner flow separation；Corner vortex；Corrected rotation speed

何成,王如根,李仁康,宋昊林,何畏,谢祥勇. 不同换算转速对高负荷风扇静子角区流动的影响[J]. 推进技术, 2017, 38(10): 2348-2357.

HE Cheng¹,WANG Ru-gen¹,LI Ren-kang¹,SONG Hao-lin¹,HE Wei²,XIE Xiang-yong³. Effects on High-Load Fan’s Flow Structure in Stator Corner under Different Corrected Rotation Speeds[J]. Journal of Propulsion Technology, 2017, 38(10): 2348-2357.

参考文献

[1] 刘大响. 航空动力发展的历史性机遇[J]. 航空发动机, 2005, 13(2): 1-3.
[2] 邵卫卫. 风扇/轴流压气机最大负荷设计技术探索[D]. 北京:中国科学院研究生院(工程热物理研究所), 2008.
[3] Cumpsty N A. Compressor Aerodynamics[M]. Florida: Krieger Publishing Company, 2004.
[4] Dring R P, Joslyn H D, Hardin L W. An Investigation of Compressor Rotor Aerodynamics[J]. Journal of Engineering for Power, 1982, 104(1): 84-96.
[5] Dring R P, Joslyn H D, Wanger J H. Compressor Rotor Aerodynamics[R]. AGARD-CP-351, 1983.
[6] Joslyn H, Dring R. Axial Compressor Stator Aerodynamics[J]. Journal of Engineering for Gas Turbines and Power, 1985, 107(3): 485-493.
[7] Schulz H, Gallus H, Lakshminarayana B. Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Partl-Quasi-Steady Flow Field and Comparsion with Steady-State Data[J]. Journal of Turbomachinery, 1990, 1(10): 669-678.
[8] Ainley D G. Performance of Axial Flow Turbine[J]. Institution of Mech, 1970, 159(2): 230-237.
[9] Lakshminarayana B, Horlock J G. Review: Secondary Flows and Losses in Cascades and Aerial-Flow Turbomachines[J]. International of Mech.Sciences, 1963, 5(3): 344-352.
[10] Horlock J H. Axial Flow Turbines[M]. London :Butterworths Press, 1966.
[11] 陶德平, 卢仁富, 赵秀华. 压气机叶栅中的二次流动[J]. 北京航空学院学报, 1982, 4(2): 77-90.
[12] 陈芳, 陈懋章, 蒋浩康. 平面叶栅端壁流的试验研究[J]. 工程热物理学报, 1988, 9(2): 125-130.
[13] Kang S. Investigation of the Three Dimensional Flow within a Compressor Cascade with and without Tip Clearance[D]. Amsterdam: Vrije Universities Brussel, 1993.
[14] 王仲奇, 冯国泰, 王松涛, 等. 透平叶片中的二次流旋涡结构的研究[J]. 工程热物理学报, 2002, 23(5): 553-556.
[15] 陈绍文, 陈浮, 郭爽, 等. 高负荷弯曲扩压叶栅中旋涡流动的研究[J]. 工程热物理学报, 2007, 28(1): 117-120.
[16] Kenneth L Suder. Blockage Development in a Transonic Axial Compressor Rotor[R]. NASA TM-113115, 1997.
[17] Chunill Hah. Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37[R]. NASA TM-215627, 2009.
[18] 吴培根. 高负荷风扇流动失稳及流动控制方法研究[D]. 西安:空军工程大学, 2014.
[19] 何成, 王如根, 胡加国, 等. 不同转速下叶尖间隙流对跨声速压气机失速的影响[J]. 推进技术, 2016, 37(9): 1657-1663. (HE Cheng, WANG Ru-gen, HU Jia-guo, et al. The Effect of Tip Leakage Flow on Compressor Instability at Different Rotation Speed [J]. Journal of Propulsion Technology, 2016, 37(9): 1657-1663.)
[20] 胡加国, 王如根, 李坤, 等. 非设计条件下跨声速压气机失速机制分析[J]. 推进技术, 2016, 37(8): 1490-1499. (HU Jia-guo, WANG Ru-gen, LI Kun, et al. Instability Mechanism Analysis with Transonic Compressor at Off-Design Work Condition[J]. Journal of Propulsion Technology, 2016, 37(8): 1490-1499.)(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2016-10-17；修订日期:2016-12-12。作者简介:何成,男,硕士生,研究领域为推进系统气动热力理论与工程。E-mail: welcomehh@126.com