TA15钛合金铣削加工表面完整性对疲劳寿命的影响  

Effect of Surface Integrity of Milling TA15 Titanium Alloy on Fatigue Life

作　　者：尉渊 赵帅 林琳 雷其平 谭继清 谭靓[2] YU Yuan;ZHAO Shuai;LIN Lin;LEI Qiping;TAN Jiqing;TAN Liang(Beijing Xinghang Electro-Mechanical Equipment Co.,Ltd.,Beijing 100074,China;Key Laboratory of High Performance Manufacturing for Aero Engine,Ministry of Industry and Information Technology of Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]北京星航机电装备有限公司,北京100074 [2]西北工业大学航空发动机高性能制造工业和信息化部重点实验室,西安710072

出　　处：《航空制造技术》2024年第11期110-117,共8页Aeronautical Manufacturing Technology

摘　　要：为优化TA15钛合金硬质合金立铣刀铣削参数,控制铣削加工表面完整性,提高构件疲劳寿命,通过铣削试验、表面完整性测试和疲劳试验,研究了TA15钛合金铣削加工表面完整性对疲劳寿命的影响。结果表明,铣削加工后TA15钛合金表面粗糙度Ra为0.148~0.245μm,最大残余压应力位于表面,残余压应力影响层深度约为30μm,硬化层深度约为70μm;疲劳寿命随着表面粗糙度的减小和表面残余压应力的增大而增大;最优的铣削工艺参数组合为:铣削速度40 m/min、每齿进给量0.03 mm/z,疲劳寿命最高为4.044×10^(5)次;拉伸断口为韧性断口,断口韧窝较深。In order to optimize the milling parameters in milling of TA15 titanium alloy using carbide end cutter,and to control the surface integrity and improve the fatigue life of components,the effects of machined surface integrity on the fatigue life of TA15 titanium alloy were investigated through milling experiments,surface integrity tests,and fatigue tests.The results show that the surface roughness Ra of TA15 titanium alloy is 0.148–0.245μm after milling,the maximum residual compressive stress is detected on the surface,the depth of the residual compressive stress affected layer is approximately 30μm,and the depth of the hardened layer is approximately 70μm.The fatigue life increases with the decrease of surface roughness and the increase of residual compressive stress.The optimal combination of milling parameters:milling speed 40 m/min,feed per tooth 0.03 mm/z,and the maximum fatigue life is 4.044×10^(5) times.The tensile fracture of the machined TA15 titanium alloy is ductile fracture with deep dimples.

关 键 词：TA15钛合金 铣削工艺参数 表面完整性 疲劳寿命 疲劳断口 

分 类 号：TG54[金属学及工艺—金属切削加工及机床]