航空发动机新旧叶片疲劳强度对比分析

发布时间：2018-03-07 20:23

本文选题：航空发动机　切入点：风扇叶片　出处：《燃气涡轮试验与研究》2016年02期 　论文类型：期刊论文

【摘要】：对航空发动机新旧风扇工作叶片进行疲劳强度对比分析,通过扫频法测定其一阶共振频率,并在一阶共振频率下对叶片进行激振,测试其对应3×107次循环时的高周疲劳极限。采用单样本t检验的方法对试验结果进行统计分析,获得风扇工作叶片新叶片对应95%置信度的疲劳极限为432.38 MPa,旧叶片对应95%置信度的疲劳极限为353.18 MPa,旧叶片的疲劳极限相对于新叶片明显降低。
[Abstract]:The fatigue strength of the new and old fan blades of aero-engine is compared and analyzed. The first order resonance frequency is measured by sweep frequency method, and the blade vibration is stimulated at the first order resonance frequency. The high cycle fatigue limit corresponding to 3 脳 107 cycles was tested. The test results were statistically analyzed by using the method of single sample t test. The fatigue limit of the new blade is 432.38 MPa, the old blade is 95% MPA, the fatigue limit of the old blade is 353.18 MPA, and the fatigue limit of the old blade is obviously lower than that of the new blade.
【作者单位】：北京101中学;中航工业沈阳发动机设计研究所;
【分类号】：V232.4

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