非对称循环加载下燃气轮机叶片材料疲劳寿命预测  

Fatigue life prediction of gas turbine blade materials under asymmetric cyclic loading

作　　者：李洪松[1] 刘永葆[1] 贺星[1] 杨涛 殷望添 LI Hongsong;LIU Yongbao;HE Xing;YANG Tao;YIN Wangtian(College of Power Engineering,Naval University of Engineering,Wuhan 430033,China;Unit No.92196,Qingdao 266000,China)

机构地区：[1]海军工程大学动力工程学院,武汉430033 [2]92196部队,山东青岛266000

出　　处：《振动与冲击》2022年第12期152-158,237,共8页Journal of Vibration and Shock

基　　金：装备预研领域基金(61400040303)。

摘　　要：燃气轮机叶片在实际工作过程中,易受到非对称循环载荷作用而发生疲劳失效。为便于准确地预测非对称循环加载下叶片材料的裂纹萌生及扩展寿命,首先考虑平均应力效应和高应力区的塑性变形影响,对Chaboche模型进行改进,然后将改进的Chaboche模型和Walker裂纹扩展公式相结合,建立了一种非对称循环载荷作用下裂纹萌生及扩展综合寿命模型,并用试验数据进行验证分析。结果表明,该模型预测得到的裂纹萌生寿命、裂纹扩展寿命与试验数据基本吻合,验证了新模型的适用性和准确性,为燃气轮机叶片损伤分析和寿命预测奠定理论基础。Gas turbine blades are susceptible to fatigue failure due to asymmetric cyclic loadsin the actual working process.In order to accurately predict the crack initiation and propagation life of the blade material under asymmetric cyclic loading,the Chaboche model was modified by considering the average stress effect and plastic deformation effect in the high-stress zone.Then a comprehensive model was established to predict crack initiation and propagation life under asymmetric cyclic loading by combining the modified Chaboche model withthe Walker’s crack propagation formula.The test data were used for verification and analysis.The results show that the crack initiation life and crack propagation life predicted by the model were consistent with the test data,which verified the applicability and accuracy of the new model.The comprehensive model lays a theoretical foundation for the damage analysis and life prediction of blades in gas turbine.

关 键 词：非对称循环载荷 燃气轮机叶片 疲劳寿命 非线性累积损伤 裂纹萌生 裂纹扩展 

分 类 号：V215.52[航空宇航科学与技术—航空宇航推进理论与工程]