Fatigue crack growth in laser-shock-peened Ti-6Al-4V aerofoil specimens due to foreign object damage
Fatigue crack growth in laser-shock-peened Ti-6Al-4V aerofoil specimens due to foreign object damage
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DOI：
10.1016/j.ijfatigue.2013.10.001
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发表时间：
2014-02-01
影响因子：
6
通讯作者：
Tong, J.
中科院分区：
文献类型：
--
作者：
Lin, B.;Lupton, C.;Tong, J.
外来物损伤（FOD）已被确定为限制风机和压气机叶片寿命的主要因素之一。本文采用实验和数值方法，对激光冲击强化（LSP）处理的Ti-6Al-4V合金通用翼型试样的疲劳裂纹扩展行为进行了全面研究。通过三维有限元分析，模拟了FOD对LSPed翼型试样的影响，并考虑了LSP和FOD引起的三维残余应力场以及压缩残余应力引起的裂纹闭合，得出了有效的应力强度因子范围。利用有效应力强度因子对低周、高周及高低周复合疲劳状态下复杂残余应力场中的疲劳裂纹扩展进行了合理分析。(C) 2013 Elsevier Ltd.版权所有。
Foreign object damage (FOD) has been identified as one of the primary life limiting factors for fan and compressor blades. A comprehensive study is reported here on the fatigue crack growth behaviour in a generic aerofoil specimen of Ti-6Al-4V alloy treated by laser shock peening (LSP) prior to FOD, using both experimental and numerical approaches. 3D finite element analyses have been carried out to simulate the FOD impact on the LSPed aerofoil specimen and to derive an effective stress intensity factor range, considering both the 3D residual stress fields due to LSP and FOD and crack closure due to the compressive residual stresses. The effective stress intensity factor was then used to provide a rational analysis of fatigue crack growth in a complex residual stress field under low cycle, high cycle and combined low and high cycle fatigue condition. (C) 2013 Elsevier Ltd. All rights reserved.