结果表明，叶片的断裂模式为振动疲劳，叶片榫头与榫槽配合不当是萌生疲劳裂纹的主要原因。
The results show that the fracture mode of blade is vibration fatigue and the main cause of initiation of fatigue crack is the mismatch between rabbet and tongue-and-groove.
将边界元分析应用于航空发动机轮盘榫槽与叶片样头联接的计算，并与激光散斑法的实测结果进行比较；
A numerical analysis of dovetail joints is made, and the results are compared with that of laser-speckles measuring.
结果表明叶片高应力区域位于榫齿及其圆弧过渡处，并且发现在这些位置存在严重的应力集中情况。
The results show that high stress in serration and its arc transition region, and observed that severe stress concentration in these locations.
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