Three-dimensional turbine blade creep life prediction method and prediction system

The invention belongs to the field of aero-engines, and particularly relates to a three-dimensional turbine blade creep life prediction method and prediction system. The maximum damage position of the three-dimensional turbine blade total model is obtained, and the creep life of a sub-model is calculated with the maximum damage position as the sub-model; the creep life of the sub-model is the creep life of the three-dimensional turbine blade. According to the method, the model is simple in structure, the structured grids are easy to divide, the large stress gradient is avoided, analysis non-convergence is avoided, the calculation cost is lower, and the turbine blade creep life with high accuracy can be obtained. 本发明属于航空发动机领域，具体涉及一种三维涡轮叶片蠕变寿命预测方法及预测系统。获得三维涡轮叶片总模型的最大损伤位置，以最大损伤位置为子模型计算子模型的蠕变寿命；所述子模型的蠕变寿命即为三维涡轮叶片的蠕变寿命。本发明方法中的模型结构简单，易于划分结构化网格，避开了较大的应力梯度，避免了分析不收敛，计算成本更低，且能够获得精确度高的涡轮叶片蠕变寿命。