涡轮盘合金氧化-疲劳裂纹扩展机理和寿命预测研究进展  

Progress on Oxidation-fatigue Crack Propagation Mechanisms and Life Prediction in Turbine Disc Alloys

作　　者：江荣 吴常皓 万煜伟 张禄 宋迎东[1,2,3] JIANG Rong;WU Changhao;WAN Yuwei;ZHANG Lu;SONG Yingdong(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016;Key Laboratory of Aero-Engine Thermal Environment and Structure,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016;State Key Laboratory of Mechanics and Control Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]南京航空航天大学航空发动机热环境与热结构工业和信息化部重点实验室,南京210016 [3]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《机械工程学报》2021年第16期122-131,共10页Journal of Mechanical Engineering

基　　金：国家自然科学基金(11872204);江苏省自然科学基金(BK20180434)资助项目。

摘　　要：航空发动机涡轮盘在其服役过程中往往在高温燃气环境下承受热载荷和机械载荷共同作用,最终因疲劳、蠕变以及氧化的交互作用而失效。随着高推重比航空发动机的发展和涡轮前温度的提高,氧化损伤对涡轮盘表面疲劳裂纹扩展的影响愈加显著,往往可使疲劳裂纹扩散速率提高1~2个数量级。综述氧化损伤对涡轮盘用高温合金疲劳裂纹扩展的影响以及疲劳裂纹尖端氧化损伤机理,分析裂纹尖端疲劳损伤、氧化损伤和动态脆化影响裂纹扩展的竞争机制,梳理考虑氧化损伤效应的疲劳裂纹扩展模型和数值模拟方法,对实现氧化-疲劳载荷作用下裂纹扩展速率的准确预测所还需开展的工作进行展望,以期有助于促进航空发动机涡轮盘损伤容限设计方法和工具的发展。During the duty cycle of the aeroengines, turbine discs are subjected to cyclic thermal and mechanical loads, which usually cause failure in turbine discs due to the interaction between fatigue, creep and oxidation. With the development of high thrust-to-weight aeroengines and the increase of turbine inlet temperature, effects of oxidation damage on the fatigue crack propagation at the turbine disc surface become more and more significant, and it usually results in an increase of fatigue crack growth rate by one-two orders of magnitude. The effects of oxidation damage on fatigue crack propagation and the oxidation mechanisms at the crack tip in turbine disc alloys are reviewed, and the competing effects of fatigue damage, oxidation damage and dynamic embrittlement at the crack tip on crack propagation are analyzed. The fatigue crack propagation numerical models and simulation methods that incorporate the effects of oxidation damage are assessed, and the work to be conducted to realise high accuracy fatigue crack propagation life prediction is proposed, which is expected to be useful to promote the development of aeroengine turbine disc damage tolerance design methods and tools.

关 键 词：镍基高温合金 疲劳裂纹扩展 裂纹尖端 氧化损伤 寿命预测 

分 类 号：TG156[金属学及工艺—热处理]