激光冲击强化对外物损伤叶片前缘的疲劳强度影响研究  

Effects of laser shock peening on fatigue strength of blade leading edge with foreign object damage

作　　者：陆炜鑫 胡殿印 鄢林 毛建兴[1,2,3] 郭小军 单晓明 张永康 王荣桥 LU Weixin;HU Dianyin;YAN Lin;MAO Jianxing;GUO Xiaojun;SHAN Xiaoming;ZHANG Yongkang;WANG Rongqiao(Research Institute of Areo-Engine,Beihang University,Beijing 100191,China;Beijing Key Laboratory of Aero-Engine Structure and Strength,Beihang University,Beijing 100191,China;United Research Center of Mid-Small Aero-Engine,Beijing 100191,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;School of Electro-Mechanical Engineering,Guangdong University of Technology,Guangzhou 510006,China)

机构地区：[1]北京航空航天大学航空发动机研究院,北京100191 [2]北京航空航天大学航空发动机结构强度北京市重点实验室,北京100191 [3]中小型航空发动机联合研究中心,北京100191 [4]北京航空航天大学能源与动力工程学院,北京100191 [5]中国航发湖南动力机械研究所,湖南株洲412002 [6]广东工业大学机电工程学院,广东广州510006

出　　处：《推进技术》2024年第4期201-209,共9页Journal of Propulsion Technology

基　　金：国家自然科学基金(52022007,51905020,52275142);国家科技重大专项(J2019-IV-0009-0077)。

摘　　要：为研究激光冲击强化对某型离心叶轮外物损伤后疲劳强度的影响,设计了反映真实叶片前缘部位的特征模拟件,并结合空气炮法模拟外物损伤,对比有/无激光冲击强化模拟件的高周疲劳试验结果,发现经激光冲击强化处理后,模拟件的疲劳强度提高约37%。同时,开展了激光冲击强化以及外物损伤后的残余应力/应变场数值仿真,结合Kitagawa-Takahashi(K-T)图法建立了考虑外物损伤与激光冲击强化的疲劳强度预测方法,与试验结果相比平均误差为7.3%,验证了方法的有效性。In order to study the effects of laser shock peening on the fatigue strength of a centrifugal impeller after foreign object damage,a characteristic simulation specimen reflecting the real leading edge of the blade was designed,combined with the air cannon method to simulate the foreign object damage.By comparing the high-cycle fatigue test results of the simulated specimens with and without laser shock peening,it is found that the fatigue strength of the simulated parts increased by about 37%after laser shock peening.At the same time,numerical simulation of residual stress/strain field after laser shock peening and foreign object damage was carried out.Combined with Kitagawa-Takahashi(K-T)diagram,a fatigue strength prediction method considering foreign object damage and laser shock peening was established.Compared with the experimental results,the average error is 7.3%,which verified the effectiveness of the method.

关 键 词：离心叶轮 叶片前缘 外物损伤 激光冲击强化 疲劳强度 K-T图法 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]