Life prediction based on the damage mechanics of aero-engine turbine blades is crucial for performing their strength design and ensuring the operational reliability under combined high and low cycle fatigue (CCF) loadings. In view of this, a simple and efficient life prediction method is developed to consider the interaction of high cycle fatigue (HCF) and low cycle fatigue (LCF) without any additional material constants, and as a basis of that a new nonlinear damage accumulation model is proposed by introducing threshold damage of the component related to material type and current HCF damage. In order to validate the presented methodology, model predictions were compared with the experimental data sets of turbine blades and its alloy materials. The predicted results indicate that the simple life prediction model is capable of estimating the fatigue life quickly with an acceptable accuracy in contrast to other four existing ones. Moreover, the threshold damage-based method provides the higher prediction accuracy than others due to improved HCF damage determined by the damage threshold.

基于航空发动机涡轮叶片损伤力学的寿命预测对于执行其强度设计和确保在高低周疲劳（CCF）联合载荷下的运行可靠性至关重要。鉴于此，开发了一种简单有效的寿命预测方法，在没有任何附加材料常数的情况下考虑高周疲劳（HCF）和低周疲劳（LCF）的相互作用，并以此为基础建立新的非线性损伤累积模型通过引入与材料类型和当前 HCF 损坏相关的组件阈值损坏来提出。为了验证所提出的方法，将模型预测与涡轮叶片及其合金材料的实验数据集进行了比较。预测结果表明，与其他四个现有模型相比，简单寿命预测模型能够以可接受的精度快速估计疲劳寿命。此外，由于改进了由损伤阈值确定的 HCF 损伤，基于阈值损伤的方法提供了比其他方法更高的预测精度。