基于POD方法的对转压气机叶顶非定常流场分析  

Analysis of tip unsteady flow field in a counter-rotating compressor based on POD method

作　　者：王磊[1,2] 高丽敏[1,2] 茅晓晨[1,2] 郭彦超[1,2] 俞一波 WANG Lei;GAO Limin;MAO Xiaochen;GUO Yanchao;YU Yibo(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;The National Key Laboratory of Aerodynamic Design and Research,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]西北工业大学翼型、叶栅空气动力学国家级重点实验室,西安710129

出　　处：《航空动力学报》2025年第2期46-60,共15页Journal of Aerospace Power

基　　金：国家自然科学基金(52106057);国家科技重大专项(J2019-Ⅱ-0016-0037);国家自然科学基金重大专项(51790512);国家级重点实验室稳定支持项目(D5050210015)。

摘　　要：为深入研究对转压气机内的非定常流动特征及其流动机理,基于非定常数值模拟和本征正交分解(POD)方法开展了对转压气机近失速工况下的叶顶非定常流场分析。结果表明:上游转子(R1)叶顶非定常流场的主导频率为1BPF(叶片通过频率),其主导结构主要是由下游势流的影响以及相邻叶片叶尖泄漏流及二次泄漏流冲击作用导致的,并且下游转子(R2)的势流作用对转子R1的非定常流动影响较大;在转子R2叶顶流场中,POD方法成功捕捉到了叶片前缘进口通道处由泄漏流溢流所导致的主要流动结构,其主导频率为0.8BPF,并且在转子R2非定常流场中起主导作用。同样转子R2受到两排转子干涉的影响,模态的主导频率为1BPF。此外,通过POD模态进行叶顶流场重构进一步反映出了对非定常流场起主导作用的流动结构。In order to investigate the unsteady flow characteristics and its flow mechanism in a counter-rotating compressor,a two-stage counter-rotating compressor was used as the research object,and the tip unsteady flow field analysis was carried out under the near-stall condition of the counter-rotating compressor based on the unsteady numerical simulation method in combination with the proper orthogonal decomposition(POD)method.The results showed that 1BPF(blade passing frequency)under near-stall conditions was taken as the dominant frequency of tip unsteady flow field in the upstream rotor,and its dominant structure was mainly caused by the influence of downstream potential flow and the impact of leakage flow and secondary leakage flow from the adjacent blade tip.Moreover,the potential flow of the downstream rotor had a greater influence on the unsteady flow in rotor R1.In the tip flow field in rotor R2,the POD modes succeeded in capturing the dominant flow structure at the inlet passage of the blade leading edge caused by spillage from the leakage flow with a dominant frequency of 0.8BPF,which played a dominant role in the unsteady flow field of rotor R2.Similarly,rotor R2 was affected by the interference of the two rotor rows,with a dominant frequency of 1BPF.In addition,the tip flow field reconstructed by the POD modes further reflected the dominant flow structure of unsteady flow field.

关 键 词：对转压气机 本征正交分解(POD)方法 非定常流场 POD模态 近失速流场 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]