摘要
涡轮盘作为航空发动机核心部件之一,在复杂交变载荷下易发生疲劳失效。开展其疲劳寿命可靠性分析,对预防故障、优化设计及保障发动机安全运行兼具理论价值与工程意义。通过逆向建模技术和布尔运算,构建航空发动机低压涡轮盘的三维模型,利用有限元仿真对涡轮盘进行应力应变分析确定其应力集中部位,并基于代理模型对轮心部位展开疲劳寿命可靠性分析。研究结果表明:涡轮盘的应变疲劳寿命概率密度函数呈正态分布,涡轮盘可靠度在0~2500次循环内较高,2500~4000次循环内急剧下降,5000次循环后趋近于零。
As one of the core components of an aero-engine,the turbine disk is prone to fatigue failure under complex alternating loads.The fatigue life reliability analysis of the turbine disk holds both theoretical value and engineering significance for preventing failure,optimizing design,and ensuring safe engine operation.In this study,a three-dimensional model of aero-engine low-pressure turbine disk is constructed using reverse modeling technology and Boolean operations.The stress-strain analysis of the turbine disk is carried out to determine its stress-concentration areas by using a finite element simulation,and the fatigue life reliability analysis is conducted for the disk hub based on the surrogate model.The results show that the probability density function of the strain fatigue life for the turbine disk follows a normal distribution,and the reliability of the turbine disk remains higher within 0~2500 cycles,decreases sharply between 2500~4000 cycles,and approaches zero after 5000 cycles.
作者
李静
葛会俊
杨智博
王瑶瑶
方鹏亚
LI Jing;GE Huijun;YANG Zhibo;WANG Yaoyao;FANG Pengya(Zhengzhou University of AeronauticsSchool of Aeroengine,Zhengzhou 450046,China;Chengdu Aircraft Industry(Group)Co,LTD,Chengdu 610092,China)
出处
《郑州航空工业管理学院学报》
2025年第5期36-42,共7页
Journal of Zhengzhou University of Aeronautics
基金
河南省科技攻关项目(242102320223)
郑州航空工业管理学院研究生教育创新计划基金项目(2024CX67)。
关键词
涡轮盘
有限元仿真
疲劳寿命
可靠性分析
turbine disk
finite element simulation
fatigue life
reliability analysis
