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航空发动机叶片高频模态阻尼的实验测试方法

郭雪莲 范雨 李琳

郭雪莲, 范雨, 李琳. 航空发动机叶片高频模态阻尼的实验测试方法[J]. 航空动力学报, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013
引用本文: 郭雪莲, 范雨, 李琳. 航空发动机叶片高频模态阻尼的实验测试方法[J]. 航空动力学报, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013
GUO Xue-lian, FAN Yu, LI Lin. Experimental test method for high-frequency modal damping of turbomachinery blades[J]. Journal of Aerospace Power, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013
Citation: GUO Xue-lian, FAN Yu, LI Lin. Experimental test method for high-frequency modal damping of turbomachinery blades[J]. Journal of Aerospace Power, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013

航空发动机叶片高频模态阻尼的实验测试方法

doi: 10.13224/j.cnki.jasp.2014.09.013
详细信息
    作者简介:

    郭雪莲(1977-),女,辽宁辽阳人,博士生,主要从事旋转机械的气动阻尼及流固耦合动力学研究.

    通讯作者:

    李琳(1956-),女,河北唐山人,教授、博士生导师,博士,主要从事结构动力学研究.E-mail:feililin@buaa.edu.cn

  • 中图分类号: V232.4;O329

Experimental test method for high-frequency modal damping of turbomachinery blades

  • 摘要: 以NASA Rotor37叶片为对象,研究了航空发动机叶片的高频模态阻尼比的实验测试方法.实验分析和数值计算均说明:在随机声激励下获得频响曲线将包含由支撑结构振动造成的峰值.基于此提出在支撑结构上布置多个传感器的实验方案,并以支撑结构的振动峰值位置和能量相对大小来判定叶片振动主导的振动峰值.用小波阈值收缩法和曲线拟合法对这些振动峰值进行了降噪和模态阻尼比识别,给出了实测模型在10kHz内“叶片主导振动”的模态阻尼比.结果表明:一般的结构金属材料条件下,叶片结构的高频模态阻尼比的数量级小于1%,且随频率增加呈下降趋势.

     

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出版历程
  • 收稿日期:  2013-06-08
  • 刊出日期:  2014-09-28

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