针对航空发动机粉末冶金旋转盘件的疲劳裂纹扩展特性，以标准紧凑拉伸试样裂纹扩展数据为基础，基于Paris公式获得了材料典型温度下的裂纹扩展参数，并利用简单件对所采用的裂纹扩展计算方法进行了验证。进行了粉末冶金旋转构件的裂纹扩展试验，继而进行断口分析，通过测量疲劳条带获得了裂纹扩展寿命。同时，采用有限元方法计算出粉末冶金构件的裂纹扩展寿命，与实测值吻合较好，验证了裂纹扩展寿命分析方法的有效性及实用性。
To study the fatigue crack propagation behaviour of powder metallurgy disc in aero-engine, based on the testing of standard compact tension samples, the parameters of Paris equation for working temperature was obtained, and the crack propagation life under complex stress state was also calculated. Then the testing of crack propagation of PM component was carried out until fracture, and fatigue stripes were measured to distinguish the propagation life from total life. At the same time, finite element method was chosen to evaluate the propagation life of the PM component under complex stress state. Agreement of the computing results with the experimental data indicated the veracity and the feasibility of the method.
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