基于临界平面法两种打孔工艺单晶涡轮叶片高周疲劳寿命对比研究  

Comparative study on high cycle fatigue life of single crystal turbine blades with two drilling techniques based on critical plane method

作　　者：张泉 徐元铭[2] 刘春红 盖玉新 魏子凡 ZHANG Quan;XU Yuanming;LIU Chunhong;GAI Yuxin;WEI Zifan(AVIC Changcheng Institute of Metrology&Measurement,Beijing 100095,China;Beihang University,Beijing 100191,China)

机构地区：[1]中国航空工业集团公司北京长城计量测试技术研究所,北京100095 [2]北京航空航天大学,北京100191

出　　处：《计测技术》2024年第6期39-49,共11页Metrology & Measurement Technology

基　　金：航空创新基金项目(ZC02402280)。

摘　　要：为研究飞秒激光打孔和电火花打孔工艺对镍基单晶涡轮叶片高周疲劳寿命的影响,分别建立两种打孔方式的有限元模型。在有限元计算过程中,结合镍基单晶本构特点和晶体塑性滑移理论,编写单晶本构模型的用户材料子程序(User Defined Material Mechanical Behavior,UMAT),计算得到高周疲劳边界条件下镍基单晶各个滑移面上的分切应力分布。针对特定应力状态下开动的滑移系和滑移面,基于临界平面法建立不同的损伤判据。选取适用于飞秒激光打孔和电火花打孔工艺镍基单晶涡轮叶片的损伤判据,分别建立高周疲劳寿命预测模型,预测两种打孔方式单晶试件和单晶涡轮叶片的高周疲劳寿命,并与实际高周疲劳试验结果进行对比,计算得到的试件和涡轮叶片的寿命预测结果与试验寿命对比误差在10%左右。研究成果为优化航空发动机涡轮叶片加工工艺提供了借鉴。In order to study the effects of femtosecond laser drilling and electrical discharge machining(EDM)drilling on high cycle fatigue life of nickel based single crystal turbine blade,finite element models for two drilling methods were established respectively.In the process of finite element calculation,combined with the constitutive characteristics of nickel based single crystal and the crystal plastic slip theory,the user defined material mechanical behavior(UMAT)of the single crystal constitutive model was written,and the shear stress distribution on each sliding surface of nickel based single crystal under high cycle fatigue boundary conditions was calculated.Based on the critical plane method,different damage criteria were established for the sliding system and sliding surface under specific stress state.The damage criteria of nickel based single crystal turbine blade suitable for femtosecond laser drilling and EDM drilling were selected,and the high cycle fatigue life prediction models were established respectively.The high cycle fatigue life of single crystal specimen and single crystal turbine blade with two drilling methods were predicted,and compared with the actual high cycle fatigue test results.The comparison error between the calculated life prediction results and the experimental life was about 10%.The research results provide a reference for optimizing the processing technology of aeroengine turbine blades.

关 键 词：高周疲劳 疲劳寿命 临界平面法 镍基单晶 气膜孔 

分 类 号：TB93[一般工业技术—计量学] V232.4[机械工程—测试计量技术及仪器]