The reason for the difference in fatigue performance of TC17 titanium alloy circular perforated plate specimens
摘 要
TC17钛合金圆形开孔平板试样的疲劳性能存在差异,采用扫描电镜和能谱分析、金相检验、残余应力测试、粗糙度检测等方法对差异原因进行分析。结果表明:对于Kt=2.52且疲劳寿命较短的板状圆孔疲劳试样,其疲劳裂纹起源于孔边倒圆角加工损伤或孔内壁加工损伤处,寿命较长试样的疲劳裂纹均起源于孔内壁亚表面;对于Kt=2.1且疲劳寿命较短的板状圆孔疲劳试样,其疲劳裂纹起源于孔内壁加工损伤或孔边倒圆角损伤处,而寿命较长试样的疲劳裂纹多起源于表面加工缺陷或孔内壁亚表面处;试样加工损伤、孔内壁较大残余压应力以及残余应力较分散等因素造成了试样的疲劳性能存在较大差异。
Abstract
The fatigue properties of TC17 titanium alloy circular perforated plate specimens were different. The reason for the differences was analyzed by scanning electron microscopy and energy spectrum analysis, metallographic examination, residual stress test and roughness test. The results show that for the plate-shaped circular hole fatigue specimen with Kt=2.52 and short life, the fatigue crack originated from the processing damage at the rounding of the hole edge or the processing damage of the inner wall of the hole, and the fatigue cracks of the longer life specimen originated from the inner wall of the hole. For the plate-shaped hole fatigue specimen with Kt=2.1 and short life, the fatigue crack originated from the machining damage of the inner wall of the hole or the rounding damage of the hole edge, while the fatigue cracks of the long-life specimen mostly originated from the surface machining defects or the subsurface of the inner wall of the hole. The fatigue properties of the samples were greatly different due to the processing damage of the samples, the large residual compressive stress on the inner wall of the hole and the dispersion of the residual stress.
中图分类号 TB31 TG115.5 DOI 10.11973/lhjy-wl202304009
所属栏目 质量控制与失效分析
基金项目
收稿日期 2022/6/13
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备注彭霜(1989-),女,硕士,工程师,主要从事航空发动机金相检验与失效分析工作,15921579734@163.com
引用该论文: PENG Shuang,SUN Zhijun,JIN Yi,TENG Yuefei,CAO Wei. The reason for the difference in fatigue performance of TC17 titanium alloy circular perforated plate specimens[J]. Physical Testing and Chemical Analysis part A:Physical Testing, 2023, 59(4): 31~37
彭霜,孙智君,金一,滕跃飞,曹玮. TC17钛合金圆形开孔平板试样疲劳性能差异原因[J]. 理化检验-物理分册, 2023, 59(4): 31~37
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【3】詹平,谢善,李欣.TC6钛合金压气机叶片裂纹产生原因[J].理化检验(物理分册),2021,57(10):43-46.
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【5】LIAO D,ZHU S P,CORREIA J A F O,et al.Recent advances on notch effects in metal fatigue:a review[J].Fatigue & Fracture of Engineering Materials & Structures,2020,43(4):637-659.
【6】田伟,伏宇,钟燕,等.缺口对TC17钛合金拉伸性能和低周疲劳性能的影响[J].材料热处理学报,2016,37(11):68-72.
【7】何杉,杨清,闵祥禄.喷丸强化对TC17钛合金疲劳性能的影响[J].金属热处理,2018,43(6):159-161.
【8】王欣,胡云辉,付书红,等.喷丸强度对TC17及GH4169合金表面完整性和高温疲劳性能的影响[J].金属热处理,2018,43(1):67-71.
【9】徐松超.喷丸强化TC17钛合金表面完整性及疲劳性能研究[D].大连:大连理工大学,2021.
【10】郭萍,潘浩,贾国玉,等.高载荷条件下TC17钛合金常规低周疲劳和保载疲劳损伤行为[J].稀有金属材料与工程,2022,51(1):301-305.
【11】李久楷,刘永杰,王清远,等.TC17钛合金高温超高周疲劳实验[J].航空动力学报,2014,29(7):1567-1573.
【12】JIAO L,QIAO S R,ZHANG C Y,et al.Fatigue properties of Ti17 alloy strengthened by combination of electric spark treatment with ultrasonic surface treatment[J].Rare Metal Materials and Engineering,2010,39(12):2091-2094.
【13】宋昌平,王金龙.表面粗糙度对TC17疲劳失效影响的试验研究[J].机械设计,2021,38(5):104-109.
【14】王金龙,高斯博,杨宇星,等.航空发动机用钛合金TC17疲劳失效研究[J].哈尔滨工程大学学报,2021,42(8):1203-1208.
【15】WANG J L,PENG W J,YU J,et al.Effect of surface roughness on the fatigue failure and evaluation of TC17 titanium alloy[J].Materials Science and Technology,2021,37(3):301-313.
【16】侯保义.机械加工纹路对材料疲劳性能的影响[J].航空制造工程,1994(3):13-14.
【17】常帅,谈建平,张剑睿,等.加工残余应力对Ti-6Al-4V试样高周疲劳性能的影响[J].压力容器,2021,38(8):7-13,28.
【18】郑程,李凯,陆慧.TC4钛合金应变疲劳试样的机加工工艺及疲劳试验[J].理化检验(物理分册),2018,54(8):582-586.
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