基于分布激励突卸的转子叶片阻尼比试验

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. 

Damping ratio experiment study on rotary blade based on distributing excitation unloaded instantaneously

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 results were analyzed.It shows that the correlations between DEUI and the other two methods are more than 75%,and without interferences of frequency resolution and power spectrum analysis error,DEUI is more accurate.