摘要
在梳理某压气机试验器开展的历次压气机性能试验结果基础上,分析了试验系统发生的若干典型异常气动物理现象,通过试验数据表征分析与抑制方法试验验证,初步揭示了压气机试验异常气动现象的形成机制.研究结果表明:进口局部导叶角度失调会对下游流场产生扰动,导致压气机性能与稳定性出现恶化;转子顶部容腔通道逆流是导致压气机转子前外壁静压测量值偏高的原因,通过抑制容腔逆流可以改善压气机气动性能;改变进口节流比观察换算流量是否发生变化,是判定压气机试验进气系统漏气问题的有效方法.研究结果对于指导压气机性能试验故障诊断和提高试验分析能力具有重要作用.
Based on arranging all previous axial flow compressor performance experimental results carried out on a compressor experimental facility,some typical abnormal aerodynamic physical phenomena presented in the experimental system were analyzed.Through analyzing experimental data and validating suppression methods,the formation mechanism of these compressor experimental abnormal aerodynamic phenomena was revealed initially.The research results indicate that the partial inlet guide vanes angle maladjustment produces disturbance on the outlet flow field,and lead to the performance and stability of the compressor deterioration.The inverse flow air occurred at the tip cavity channel of the compressor first rotor is the reason that the measurement value of the out wall static pressure is high before the first rotor.By inhibiting the inverse flow,the compressor aerodynamic performance can improve.The change of corrected mass flow versus the inlet throttling ratio,which is the ef-fective method to determine the leakage problem of compressor experimental intake system.The research results can play an important role on guiding compressor performance experimental fault diagnosis and improving experimental analysis ability.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第3期639-646,共8页
Journal of Aerospace Power
关键词
轴流压气机
气动性能
进口导叶安装角
泄漏流
进口节流比
axial flow compressor
aerodynamic performance
inlet guide vane angle
leakage flow
inlet throttling ratio
