复合材料机匣周向安装边模拟件强度与损伤分析

为了较准确地预测航空发动机机匣复合材料周向安装边的强度和失效模式,以某型涡扇发动机复合材料机匣周向安装边为对象,开展了复合材料机匣周向安装边模拟件的静拉伸试验和静强度及损伤预测方法研究。通过试验获得周向安装边模拟件静强度及给定考核静载下的损伤模式;基于3维逐渐损伤分析方法,采用挤压孔边局部节点合并等效接触算法,建立了复合材料机匣周向安装边模拟件的静载逐渐损伤分析模型,采用该模型对安装边模拟件不同角度的铺层损伤模式进行了分析。结果表明:静强度预测误差在6%以内,考核静载下的预测损伤与试验结果对比损伤区域基本一致;所建立的静载逐渐损伤分析模型具有较高的计算精度。

Analysis of Static Strength and Damage of Circumferential Mounting Flange Simulators in Composite Casing

In order to accurately predict the strength and damage mode of the circumferential mounting flange in the composite casing of a turbofan engine,taking the circumferential mounting flange in the composite casing of a turbofan engine as an object,the static tensile tests and the prediction method of static strength and damage of the circumferential mounting flange simulators in composite casing were carried out.The static strength of the circumferential mounting flange simulators and the damage mode under static load were obtained by experiments.Based on the three-dimensional progressive damage analysis method and the equivalent contact algorithm of node combination,the static load progressive damage analysis model of circumferential mounting flange simulator in composite casing was established.Compared with the test results,the predicting error of static strength is less than 6%.And the damage area under static load is basically the same.Based on the established method,the damage modes of the layer at different angles were analyzed.The analysis shows that the static load progressive damage analysis model established has high calculation accuracy.