钛合金缺口试样拉伸破坏载荷预测

针对航空发动机轮盘常用钛合金材料,开展了常温和高温下光滑和缺口试样的拉伸变形和断裂行为试验研究,建立了其大变形本构模型。基于该本构模型,利用大变形有限元分析,计算获得缺口试样的载荷-位移曲线。将该曲线最高点对应的载荷确定为试样的拉伸破坏载荷,并与试验进行对比。结果表明理论预测与试验吻合较好,从而验证了所提出的拉伸破坏载荷预测方法的有效性。

Prediction of Broken Load for Notched Specimen of Titanium Alloy

The tensile deformation and fracture behavior tests under both room and high temperature are conducted on notched specimens of titanium alloy used commonly in aeroengine disc. Then a large deformation constitutive model is established. Based on the constitutive model, load-displacement curves of notched specimens are obtained by large deformation finite element analysis. The tensile broken load is defined as the value at the highest point of load-displacement curve. The predicted tensile broken loads are compared with the tests, and the theoretical predicted values are in good agreement with experimental ones. The results show that the proposed method for predicting tensile broken load is valid.