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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。
Aiming at the fatigue crack propagation characteristics of powder metallurgy rotating disc of aeroengine, based on the crack propagation data of a standard compact tensile specimen, the crack propagation parameters at a typical temperature of the material are obtained based on the Paris formula, and the cracks Extended calculation method was verified. The crack propagation test of the powder metallurgy rotating component was carried out, and then the fracture analysis was carried out. The fatigue life of the crack was obtained by measuring the fatigue band. At the same time, the crack propagation life of the powder metallurgy component is calculated by the finite element method, which is in good agreement with the measured value, which verifies the validity and practicability of the crack propagation life analysis method.