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使用有限元的方法,建立了某航空发动机机匣安装座处局部模型,计算得到了不同尺寸裂纹的应力强度因子的形状因子Y.基于BS7910评定方法,利用失效评估图(FAD,Failure Assessment Diagram)确定了机匣安装座结构在工作应力下的可接受裂纹尺寸为84.8 mm,结构的剩余强度随裂纹尺寸的增加而显著降低,焊缝较母材具有更低的损伤容限和剩余强度.使用缩小宽度模拟验证件模拟工作状态载荷进行了验证试验,当裂纹尺寸与试样宽度比值较小时,与模拟验证件的评估结果基本吻合.根据Paris公式,构件在工作应力下的剩余寿命为74238周次.
Using the finite element method, a local model of the mounting seat of aeroengine was established, and the shape factor Y of the stress intensity factor of different size cracks was calculated.According to the BS7910 evaluation method, the failure assessment diagram (FAD) The acceptable crack size of the box mount structure under working stress is determined to be 84.8 mm, the residual strength of the structure decreases significantly with the increase of the crack size, and the weld has lower damage tolerance and residual strength than the base metal. According to the Paris formula, the residual life under the working stress is 74238 weeks according to the formula of Paris, which is the same as that of the simulation test. Times.