外物损伤对叶片振动疲劳裂纹扩展性能的影响  

Effect of Foreign Object Damage on Vibration Fatigue Crack Propagation of Blades

作　　者：杨硕 杜天玮 张晓鹏 马梁 张桂昌 YANG Shuo;DU Tianwei;ZHANG Xiaopeng;MA Liang;ZHANG Guichang(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;College of Aeronautical Engineering,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实验室,天津300222 [3]中国民航大学航空工程学院,天津300300

出　　处：《兵工学报》2023年第6期1713-1721,共9页Acta Armamentarii

基　　金：天津市自然科学基金项目(18JCQNJC75300)。

摘　　要：为研究外物损伤(FOD)对航空发动机叶片的疲劳裂纹扩展影响,基于落锤冲击试验系统,在不同冲击能量下进行TC4钛合金试件的FOD模拟试验及振动疲劳试验,获得损伤试件的裂纹长度与疲劳寿命的关系,并拟合疲劳断口裂纹形貌参数,建立疲劳裂纹扩展寿命预测计算模型。研究结果表明:损伤缺口的深度和宽度随冲击能量的减小而非线性的减小。当冲击能量较大时,试件的疲劳裂纹先沿弯曲微裂纹扩展,后沿直线扩展;当冲击能量较小时,试件疲劳裂纹保持直线扩展。裂纹的萌生寿命与冲击能量、应力水平二者相关。In order to study the effect of foreign object damage(FOD)on the fatigue crack propagation of aero-engine blades,using the drop weight impact testing equipment,the FOD simulation test and vibration fatigue test of TC4 titanium alloy specimens were carried out under different impact energies.The relationship between the crack length and fatigue life of the damaged specimens was obtained,and the parameters of fatigue fracture crack morphology were fitted to establish a fatigue crack growth prediction and calculation model.The results showed that:The depth and width of the notch decreased nonlinearly with the decrease of impact energy;when the impact energy is large,the fatigue crack propagates first along the bending microcrack and then along the straight line;when the impact energy is small,the fatigue crack of the specimen keeps linear propagation;the crack initiation life is related to both impact energy and stress level.

关 键 词：外物损伤 叶片 落锤冲击 TC4钛合金 振动疲劳 裂纹扩展 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]