探针支杆对压气机转子性能及流场影响的数值模拟研究

推进技术 ›› 2016, Vol. 37 ›› Issue (12): 2288-2295.

探针支杆对压气机转子性能及流场影响的数值模拟研究

马宏伟¹,项乐²

北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191,先进航空发动机协同创新中心，北京 100191

发布日期:2021-08-15
作者简介:马宏伟，男，博士，教授，博导，研究领域为叶轮机械气动热力学。
基金资助:
国家自然科学基金(51161130525)。

Numerical Investigation of Effects of Probe Support on Performance and Flow Field of Compressor Rotor

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamic，School of Energy and Power Engineering，Beihang University，Beijing 100191，China and Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究探针支杆对压气机转子性能及流场的影响，以低速轴流压气机单转子为研究对象，利用定常和非定常计算方法分析了在转子叶片上游50%弦长位置处安装探针支杆后转子整体性能及流场结构的变化。结果表明:支杆的存在会使压气机转子设计点静压升下降1.09%，损失增大8%；近失速点静压升下降0.8%，损失增大4.2%。同时支杆尾迹会周期性改变泄漏涡的形态与强度，不会改变泄漏涡破碎导致的泄漏涡脱落频率。支杆尾迹造成的非定常效应使叶尖区域局部总压升有所升高，在近失速工况下，总压升提高更显著。

关键词: 数值模拟；探针支杆；转子；泄漏涡

Abstract: In order to study the effects of probe support on the performance and flow field of a compressor rotor，a low-speed axial compressor rotor was investigated. The overall performance and flow field of the rotor are analyzed after inserting a cylindrical probe support at 50% chord upstream from the rotor blade leading edge through steady and unsteady numerical simulation. The results indicate that the static pressure rise decrease by 1.09% at the design point and about 0.8% at near-stall point，as loss increase by 8% at design point and 4.2%at near-stall point after installing the probe support. The wake of probe support can change the shape and strength of leakage vortex periodically，but it does not change the leakage vortex shedding frequency caused by leakage vortex broken. It is also found that the unsteady effect aroused by the wake of probe support may increase the total pressure rise in the tip region，and the increment is notable in the near stall condition.

Key words: Numerical simulation；Probe support；Rotor；Leakage vortex

马宏伟,项乐. 探针支杆对压气机转子性能及流场影响的数值模拟研究[J]. 推进技术, 2016, 37(12): 2288-2295.

MA Hong-wei¹,XIANG Le². Numerical Investigation of Effects of Probe Support on Performance and Flow Field of Compressor Rotor[J]. Journal of Propulsion Technology, 2016, 37(12): 2288-2295.

参考文献

[1] Lepicovsky J. Effects of a Rotating Aerodynamic Probe on the Flow Field of a Compressor Rotor[R]. NASA/CR-2008-215215.
[2] Siakov B T, Tan C S. Effect of Upstream Unsteady Flow Conditions on Rotor Tip Leakage Flow[R]. ASME GT-2002-30358.
[3] Simon Coldrick, Paul Ivey, Roger Wells. Considerations for Using 3-D Pneumatic Probes in High-Speed Axial Rotor Compressors[J]. Journal of Turbomachinery, 2003, 125: 149-154.
[4] HE Xiang, MA Hong-wei, REN Ming-lin, et al. Investigation of the Effects of Airfoil-Probes on the Aerodynamic Performance of an Axial Compressor[J]. Chinese Journal of Aeronautics, 2012, 25(4): 517-523.
[5] 霍磊, 牛为民, 任丽芸. 尾迹对压气机转子性能的非定常数值模拟[J]. 燃气涡轮实验与研究, 2008, 21(1): 26-32.
[6] 刘火星, 周琨, 邹正平. 涡轮叶栅尾迹对二次流影响的实验研究[J]. 工程热物理学报, 2009, 30(3):397-401.
[7] 李少辉. 探针支杆对压气机下游流场的影响[D]. 北京:北京航空航天大学, 2013.
[8] MA Hongwei, WEI Wei. Experimental Investigation of Effects of Distributed Riblets on the Dynamic Performance of a Low-Speed Compressor[J]. Journal of Thermal Science, 2013, 22(6): 592-599 .
[9] HE Xiang, MA Hong-wei, ZHANG Jun, et. al. Wavelet Analysis of the Shaft Order Perturbation and Stall Inception in an Axial Compressor[J]. Journal of Thermal Science, 2013, 22(3): 223-228.
[10] 马宏伟, 蒋浩康. 压气机不同状态下转子出口三维紊流流场[J]. 航空动力学报, 1997, 12(3):268-272.
[11] 马宏伟, 蒋浩康. 压气机转子三维紊流流场. 工程热物理学报[J]. 1998, 19(3): 287-292.
[12] Vo H D, Tan C S, Greitzer E M. Criteria for Spike Initiated Rotating Stall[R]. ASME 2005-GT-68374.
[13] Park H G. Unsteady Disturbance Structure in Axial Flow Compressor Stall Inception[D]. USA: Massachusetts Institute of Technology, 1993.
[14] 刘宝杰, 张志博, 于贤君. 轴流压气机转子叶尖泄漏阻塞特性的实验研究[J]. 航空学报, 2013, 34(12):2682-2691.
[15] 茅晓晨, 刘波, 张国臣, 等. 复合弯掠优化对跨声速压气机性能影响的研究[J]. 推进技术, 2015, 36(7):996-1004. (MAO Xiao-chen, LIU Bo, ZHANG Guo-chen, et al. Effectiveness of Composite Optimization of Lean and Sweep on Transonic Compressor Performance[J]. Journal of Propulsion Technology, 2015, 36(7): 996-1004.)
[16] 张龙新, 王松涛, 阮国辉, 等. 间隙流动对低反动度跨声速转子气动性能影响[J]. 推进技术, 2015, 36(4):566-571. (ZHANG Long-xin, WANG Song-tao, RUAN Guo-hui, et al. Effects of Tip Leakage Flow on Aerodynamic Performance of a Low-Reaction Transonic Rotor[J]. Journal of Propulsion Technology 2015, 36(7): 566-571.)(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2015-07-05；修订日期:2015-10-28。基金项目:国家自然科学基金(51161130525)。作者简介:马宏伟,男,博士,教授,博导,研究领域为叶轮机械气动热力学。E-mail: mahw@buaa.edu.cn