损伤位置对发动机叶片振动疲劳的影响研究  

Study on the effect of foreign object damage position on the vibration fatigue of aeroengine blade

作　　者：杨硕 赵娜 马梁 张桂昌 张晓鹏 杜天玮 YANG Shuo;ZHAO Na;MA Liang;ZHANG Guichang;ZHANG Xiaopeng;DU Tianwei(College of Mechanical Engineering,Tianjin University of Science&Technology,Tianjin 300222,China;Tianjin Key Laboratory of Integrated Design and On-line Monitoring for Light Industry&Food Machinery and Equipment,Tianjin 300222,China;Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]天津科技大学机械工程学院,天津300222 [2]天津市轻工与食品工程机械装备集成设计与在线监控重点试验室,天津300222 [3]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《兵器装备工程学报》2023年第11期97-102,132,共7页Journal of Ordnance Equipment Engineering

基　　金：天津市教委科研计划项目(2020KJ018)。

摘　　要：为研究外物损伤冲击位置对航空发动机叶片疲劳极限的影响,基于落锤冲击试验系统,对TC4钛合金叶片模拟试件分别进行了边缘冲击和面心冲击等2种外物损伤试验;在此基础上,对缺口试件和光滑试件分别进行振动疲劳试验,获得损伤试件缺口几何特征,并得到了不同冲击位置下的TC4叶片振动疲劳极限。结果表明:面心冲击比边缘冲击造成的缺口宽度、深度、体积更大,缺口平均体积大46.7%;光滑试件疲劳裂纹的产生出现在试件缩颈处,外物损伤缺口均产生在缺口处;边缘冲击导致的叶片振动疲劳极限降低的程度反而要大于面心冲击,边缘冲击的疲劳极限较光滑试件下降了55.8%,面心冲击的疲劳极限较光滑试件下降了35.1%。In order to study the influence of the impact position of foreign object damage on the fatigue limit of the aero engine blade,based on the drop weight impact test system,two kinds of foreign object damage tests are carried out on the TC4 titanium alloy blade simulation specimens:edge impact and face-centered impact.On this basis,the vibration fatigue tests of the notched specimen and the smooth specimen are carried out respectively,and the geometric characteristics of the notched specimen of the damaged specimen are obtained,and the vibration fatigue limit of TC4 blade under different impact positions is obtained.The results show that the gap width,depth and volume caused by the face-centered impact are greater than those caused by the edge impact,with the average gap volume is 46.7%larger.The fatigue crack of the smooth specimen appears at the neck of the specimen,and the external damage gap is generated at the notch.The edge impact causes the blade vibration fatigue limit to be reduced to a greater extent than the face-centered impact.Compared with smooth specimen,the fatigue strength of edge impact decreases by 55.8%,and the fatigue strength of face-centered impact decreases by 35.1%.

关 键 词：外物损伤 冲击位置 TC4叶片 振动疲劳 疲劳极限 

分 类 号：V19[航空宇航科学与技术—人机与环境工程] V23