亚音轴流压气机转子转速对叶尖区非定常流的影响  

Influence of Different Rotor Speeds on the Unsteady Flow Near Tip Region in a Subsonic Axial Flow Compressor Rotor

作　　者：陈智洋[1] 吴艳辉[1,2] 杨国伟[1] 安光耀 王博[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]先进航空发动机协同创新中心,北京100191

出　　处：《工程热物理学报》2017年第5期993-1000,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.11572257;No.51536006;No.51276148);航空科学基金(No.2015ZB53027);西北工业大学研究生创意创新种子基金资助

摘　　要：为了探究不同转速对某亚音轴流压气机叶尖泄漏流非定常性的影响,采用动态压力测量技术获得不同转速机匣壁处压力信号。试验测量表明,在近失速工况压力信号的频谱出现表征旋转不稳定性的特征频率驼峰。其驼峰峰值处频率随转速的提高相对减小。在此基础,分别进行不同转速的多通道数值模拟。数值模拟中,叶尖区的静压监测信号频谱与试验具有一致性,转子叶尖存在逆转子传播的周向行波。该周向行波对应了试验中的旋转不稳定现象。进一步的数值模拟流场分析表明,该周向行波在53%设计转速时是源于叶顶泄漏流自我维持的非定常性。在71%设计转速时,在某些时刻泄漏涡发生破碎并参与到周向行波的形成过程。In order to explore the influence of the different rotor speed on the unsteady flow near tip region in a subsonic axial flow compressor rotor, the casing wall static pressure signals were measured by the dynamical pressure transducers at 53% and 71% design rotor speeds respectively. In the pressure frequency spectra, RIs were to be found as characteristic humps below the blade passing frequency near stall at different rotor speeds. The peak frequency of the characteristic hump shifts lower with the increase of the rotor speed. Based on the experimental measurement, the multi-passage simulations were conducted at different rotor speeds. The characteristic frequencies of the static pressure oscillations near tip region at different rotor speeds were consistent with that in measurements. It can be found that circumferential traveling waves rotated against the rotor near tip region at the two rotor speeds. The circumferential traveling waves can be regard as RI. The details of the flow fields indicated that RI originated from the self-induced of tip leakage flow at 53% design rotor speed. However, the formation of RI was accompanied by the breakdown of tip leakage vortex at 71% design rotor speed.

关 键 词：亚音压气机 轴流 非定常性 叶尖泄漏流 试验测量 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]