首页|TA15钛合金铣削加工表面完整性对疲劳寿命的影响

TA15钛合金铣削加工表面完整性对疲劳寿命的影响

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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 0.148~0.245 μm,最大残余压应力位于表面,残余压应力影响层深度约为30 μm,硬化层深度约为70 μm;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4.044×105 次;拉伸断口为韧性断口,断口韧窝较深.
Effect of Surface Integrity of Milling TA15 Titanium Alloy on Fatigue Life
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 0.148-0.245 μm after milling,the maximum residual compressive stress is detected on the surface,the depth of the residual compressive stress affected layer is approximately 30 μm,and the depth of the hardened layer is approximately 70 μm.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 4.044×105 times.The tensile fracture of the machined TA15 titanium alloy is ductile fracture with deep dimples.

TA15 titanium alloyMilling parametersSurface integrityFatigue lifeFatigue fracture

尉渊、赵帅、林琳、雷其平、谭继清、谭靓

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北京星航机电装备有限公司,北京 100074

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

TA15钛合金 铣削工艺参数 表面完整性 疲劳寿命 疲劳断口

2024

航空制造技术
北京航空制造工程研究所

航空制造技术

CSTPCD北大核心
影响因子:0.403
ISSN:1671-833X
年,卷(期):2024.67(11)