Investigation of flow unsteadiness in a highly-loaded compressor cascade using a dynamic mode decomposition method  

作　　者：Guangyao AN Yanhui WU Jinhua LANG Zhiyang CHEN Xiaobing ZHOU 

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China [2]Shaanxi Key Laboratory of Internal Aerodynamics in Aero-Engine,Xi’an 710129,China

出　　处：《Chinese Journal of Aeronautics》2022年第5期275-290,共16页中国航空学报（英文版）

基　　金：supports of National Natural Science Foundation of China(Nos.51790512,52176045);the National Major Science and technology Project of China(No.J2017-Ⅱ-0010-0024);the Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University,China(No.CX201911)。

摘　　要：Unsteady flow in the hub endwall region has long been a hot topic in the turbomachinery community.However important it is to the performance of the whole engine,the coherent unsteady flow phenomena are still not well understood.In this paper,the complex flow field in the hub endwall of a cantilevered compressor cascade has been investigated through numerical approach.The predicted results were validated by experimental data.To highlight the dominant flow structures among irregular and chaotic motions of various vortices,a Dynamic Mode Decomposition(DMD)method was utilized.The results show that there exist three dominant periodic flow structures:the oscillation of the leakage vortex,a circumferential migration of a Breakdown Induced Vortex(BIV)and the fluctuation of the passage vortex.These three coherent structures all together form a self-sustained closed loop which accounts for the flow unsteadiness of the studied cascade.During this process,the BIV plays a key role in inducing the flow unsteadiness.Only if the BIV is strong enough to affect the passage vortex,the flow unsteadiness occurs.This study expands current knowledge base of flow unsteadiness in a compressor environment,and shows the efficacy of the DMD method for revealing the origin of flow unsteadiness.

关 键 词：CASCADE COMPRESSOR Dynamic Mode Decomposition(DMD) ENDWALL Unsteady flow Vortex breakdown 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]