多级压气机失速起始点预测方法的应用  

The Application of Prediction Method for the Stall Inception Point of Multi-stage Compressors

作　　者：鲍毅超 熊珊 程凡解 冀国锋 孙大坤[1] 孙晓峰[1] BAO Yi-Chao;XIONG Shan;CHENG Fan-Jie;JI Guo-Feng;SUN Da-Kun;SUN Xiao-Feng(Beihang University School of Energy and Power Engineering,Beijing 100191,China;AECC Guiyang Institution,Guiyang 550000,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中国航发贵阳发动机设计研究所,贵阳550000

出　　处：《工程热物理学报》2019年第12期2830-2836,共7页Journal of Engineering Thermophysics

基　　金：自然科学基金资助项目(NO.51576008;No.11661141020;No.51236001)

摘　　要：本文基于所发展的多级压气机流动稳定性快速预测模型,首先应用激盘和半激盘模型对TA66低速实验台进行了失速起始点预测,并与实验结果对比,验证了模型的可靠性,讨论了不同径向模态与周向模态对预测结果的影响。进而用此模型预测了某型涡扇发动机的压气机稳定工作范围,为其稳定性设计提供依据,并逐级减少叶片排数量,观察系统稳定性变化,分析了多叶片排对系统稳定性带来的影响.Based on the developed rapid prediction model for the flow instability of multi-stage compressors,the stall inception point of TA66 low speed compressor rig is predicted by actuator disc model and semi-actuator disc model.The comparison with the experimental data demonstrates the reliability of the model and the effects of different radial and circumferential mode are discussed.The stall margin of one turbofan engine is predicted,providing gist for its stability design.The impact of multi-stage on stability is analyzed by gradually reducing the number of blade row.

关 键 词：多级压气机 非定常流动 稳定性模型 旋转失速 

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]