摘要
针对航空发动机压气机叶片动态设计中阻尼比难以估计的情况,建立了分布激励下转子叶片的响应模型,并基于此模型设计了一种分布激励突卸的非接触阻尼比试验方法.利用分布激励突卸法进行了转子叶片的前8阶阻尼比测试,对同样的转子叶片进行半功率法和模态分析法阻尼比试验,将三者的试验结果进行相关分析.结果表明,分布激励突卸法与其余两种方法的试验结果相关性大于75%,且在阻尼比试验中无频率分辨率及频谱分析误差的干扰,准确度更高.
For the difficulty of estimating damping ratios in the dynamic design of aeronautics engine compressor blade,a response model of rotary blade under distributing excitation was established,and a nonattached damping ratios testing method with distributing excitation unloaded instantaneously(DEUI) was developed on the basis of this model.The former eight resonance damping ratios were tested with DEUI as well as with half-power method and modal analysis method,while the correlations of their experimental result...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第11期2521-2526,共6页
Journal of Aerospace Power
基金
国家自然科学基金(50675099)
南京航空航天大学校青年基金(1002908715)
关键词
转子
阻尼比
试验
半功率法
分布激励突卸法
模态分析法
rotor
damping ratio
experiment
half-power method
distributing excitation unloaded instantaneously method
modal analysis method
