航空发动机涡轮盘模拟件疲劳数值仿真研究  

Study on Fatigue Numerical Simulation ofAeroengine Turbine Disk Simulator

作　　者：赵慧 宋磊 赵玮 李培尧 ZHAO Hui;SONG Lei;ZHAO Wei;LI Peiyao(School of Aircraft Engineering,Xi’an Aeronautical University,Xi’an 710077,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Steel-making Plant 2,ShanxiTaigang Stainless Steel Company,Taiyuan 030003,China;Taiyuan International Airport Co.,Ltd,Communication Navigation Department Taiyuan 030031,China)

机构地区：[1]西安航空学院飞行器学院,西安710077 [2]西北工业大学航空学院,西安710072 [3]山西太钢不锈钢股份有限公司炼钢二厂,太原030003 [4]太原国际机场有限责任公司通信导航室,太原030031

出　　处：《自动化与仪器仪表》2024年第4期25-31,共7页Automation & Instrumentation

摘　　要：航空发动机涡轮叶片长期处在高温、高压、高载荷的服役条件下,针对其经常出现的疲劳载荷导致破坏的情况,利用CATIA软件对某型航空发动机涡轮盘模拟件进行建模,借助Python语言在ABAQUS平台对模型进行参数设置,研究了涡轮盘模拟件在不同载荷和温度等工况下的力学响应,确定构件危险点并对附近的单元进行应力应变分析。然后通过相关已知数据,将计算所得结果文件导入到Fe-safe中实现交变载荷的模拟,获得疲劳寿命。利用已有镍基单晶高温合金材料S-N曲线进行对比分析,计算温度达到材料稳定临界值时的疲劳寿命,最后将两组数据对比研究危险点的寿命变化,对影响疲劳失效的主要因素进行了分析并给出了一些有益于工程结构的结论。Aeroengine turbine blades have been in service under high temperature,high pressure and high load for a long time.In view of the damage caused by fatigue load that often occurs,CATIA software is used to model a certain type of aero-engine turbine disk simulator,and Python language is used to set the parameters of the model on the ABAQUS platform,and the mechanical response of the turbine disk simulator under different load and temperature conditions is studied,Determine the dangerous points of components and conduct stress and strain analysis on the nearby elements.Then,through the relevant known data,the calculated result file is imported into Fe-safe to realize the simulation of alternating load and obtain the fatigue life.The S-N curve of the existing nickel-based single crystal superalloy material is used for comparative analysis to calculate the fatigue life when the temperature reaches the critical value of the material stability.Finally,the life changes of the dangerous points are compared and studied,and the main factors affecting the fatigue failure are analyzed and some conclusions beneficial to the engineering structure are given.

关 键 词：疲劳载荷 应力应变 仿真模拟 Fe-safe 寿命计算 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]