针对航空发动机涡轮叶片在高低周复合疲劳损伤影响下存在寿命预测困难问题,提出一种考虑耦合损伤的改进非线性累积损伤模型。在Manson-Halford (M-H)模型的基础上,结合复合材料在不同应力水平下的疲劳损伤行为,构建考虑耦合损伤的高低周复合疲劳寿命预测模型。以常用航空发动机叶片材料为例,将疲劳试验寿命数据与Miner模型、T-K模型、Zhu模型和改进M-H模型的预测寿命进行对比,验证改进M-H模型的预测精度和适用性。结果表明,改进M-H模型预测结果分散性小,预测精准度较高,对Ti-6Al-4V材料的预测结果均在2倍误差范围以内,对GH4033材料的预测86%左右的数据在2倍误差范围以内,对TC-11材料的预测结果均在1.5倍误差范围以内。本研究所提出的改进M-H模型能够更准确地描述复合材料在不同应力水平下的疲劳损伤行为,提高了疲劳寿命预测的准确性和可靠性,为航空发动机叶片强度设计、疲劳寿命预测和损伤分析提供了参考价值。

In order to solve the problem of difficulty in predicting the life of aeroengine turbine blades under the influence of high and low cycle compound fatigue damage, an improved nonlinear cumulative damage model considering coupling damage was proposed. On the basis of the Manson-Halford (M-H) model, combined with the fatigue damage behavior of the composite materials under different stress levels, a high-low and low-cycle composite fatigue life prediction model considering coupled damage is constructed. The results show that the prediction results of the improved M-H model are less dispersed and the prediction accuracy is high, and the prediction results for Ti-6Al-4V materials are within the error range of 2 times, the prediction results of about 86% of the prediction data for GH4033 materials are within the error range of 2 times, and the prediction results of TC-11 materials are within the error range of 1.5 times. The improved M-H model proposed in this study can more accurately describe the fatigue damage behavior of composite materials under different stress levels, improve the accuracy and reliability of fatigue life prediction, and provide reference value for aeroengine blade strength design, fatigue life prediction and damage analysis.

国家自然科学基金项目（52165019）,内蒙古自治区研究生科研创新项目(S20231130Z)；内蒙古自治区重点研发和成果转化计划（2023KJHZ0008、2022YFHH0055）；内蒙古自治区直属高校基本科研业务费项目（JY20220305）