摘要
基于模态分析理论,运用实验设备和ANSYS软件对某型发动机风扇叶片进行有限元模态分析,计算其在不同转速下的固有频率和振型,分析发现叶片最大变形量一般发生在叶尖或前缘处,其位置可以从模态振型图上找出;作出叶片的Campbell图以研究其振动特性,发现其在1阶、2阶范围内存在4个共振点,求取叶片在发动机不同工作状态下的转速裕度,结果表明该型风扇叶片满足10%的转速裕度要求。本方法可为发动机风扇叶片设计、性能评估和故障诊断等方面的研究提供理论依据。
A method of finite element analysis based on modality analysis theory with equipment and ANSYS software is used to study a fan blade. According to its inherent frequency and modal shapes under different speeds, the result is figured that maximum blade deformation generally occurred at the tip or on the leading edge, and its location could be found in modal shape. After making Campbell map to analyze its vibration characteristics, there are four resonance points exist in the range of first-order and second-order. The four resonance points and the blade＇s rotation margins show that the fan blade meet requirement of 10% vibration margin. This method could supply theoretical basis for blade design, performance evaluation and fault diagnosis.
出处
《中国民航大学学报》
CAS
2015年第6期13-16,共4页
Journal of Civil Aviation University of China
基金
中央高校基本科研业务费专项(ZXH2010D019)
中国民航大学科研基金项目(05yk08m)
