Effect of fore/aft-loaded rotor on compressor stability under inlet circumferential distortion  

作　　者：Dakun SUN Benhao GU Fangfei NING Dengke XU Xiaofeng SUN 

机构地区：[1]School of Energy and Power Engineering,Beihang University,Beijing 102206,China [2]Research Institute of Aero-engine,Beihang University,Beijing 102206,China

出　　处：《Chinese Journal of Aeronautics》2024年第5期199-213,共15页中国航空学报（英文版）

基　　金：The research presented here was supported by the National Natural Science Foundation of China(Nos.52306036 and 52325602);the Science Center for Gas Turbine Project,China(Nos.P2022-A-II-002-001 and P2022-C-II-003-001);the Project funded by China Postdoctoral Science Foundation(No.2022M720346);the National Science and Technology Major Projectc,China(Nos.Y2022-II-0003-0006 and Y2022-II-0002-0005);Also,the research is supported by the Key Laboratory of Pre-Research Management Centre,China(No.6142702200101);the Fundamental Research Funds for the Central Universities,China(Nos.YWF-23-Q-1009 and YWF-23-Q-1065).

摘　　要：A modified small perturbation stability prediction model for axial compressors with circumferential inlet distortions is established and applied to investigate the effect of fore/aft-loaded rotor on compressor stability under circumferentially distorted inlet conditions.The inlet total pressure distribution downstream of the distortion screen is measured in experiments and employed for simulations which are implemented via time-space spectral method.The stall inception prediction results via the stability model indicate that the compressor with aft-loaded rotor not only performs better in terms of stability under uniform inlet,but also maintains a larger stability margin under circumferentially distorted inlet.The experiments for compressors with fore-loaded and aft-loaded rotor are respectively carried out.The results validate the reliability of numerical simulations and the predicted conclusion that the aft-loaded rotor is beneficial for compressor stability.Besides,the ability of the developed theoretical model for compressor stability prediction under circumferential distortions is confirmed.In addition,dynamic pressure signals at rotor tip measured in experiments illustrate that the circumferential distortion has little effect on the compressor stall pattern.

关 键 词：Axial compressor stability Inlet distortion Blade loading Small perturbation Time-space spectral method 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]