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镍基高温合金GH4169是一种拥有优良的机械性能及抗腐蚀能力的耐热合金,被广泛应用于航空航天工程等领域,其切削过程因热力耦合作用产生的残余应力对零件的疲劳性能有重要影响。本文采用GH4169车削试验及Deform-3D仿真模拟相结合的方法,通过试验的切削力和仿真的温度-应变场对残余应力场的形成机理进行研究。结果表明:刀具磨损对主切削分力和车削温度的影响非常显著,在刀片磨钝过程中,主切削分力由538N增大到756N,剪切区温度由552℃增高到654℃,工件表面的应变由3.3升高到3.5;刀具磨损导致切削力和的温度-应变的增大,致使表面圆周和进给方向的残余拉应力峰值由517MPa、242MPa增大到860MPa、442MPa;表层残余压应力峰值-696MPa、-356MPa增大到-756MPa、-456MPa;残余应力层深度由72μm增大到85μm。
Nickel-based superalloy GH4169 is a heat-resistant alloy with excellent mechanical properties and corrosion resistance. It is widely used in aerospace engineering and other fields. The residual stress caused by thermal coupling during cutting process is important for the fatigue performance of parts influences. In this paper, the combination of GH4169 turning test and Deform-3D simulation is used to study the formation mechanism of residual stress field through the experimental cutting force and simulated temperature-strain field. The results show that the influence of tool wear on the main cutting component and turning temperature is very significant. During the blade blunting process, the main cutting component increases from 538N to 756N, the shear zone temperature increases from 552 to 654 ℃, and the workpiece surface Of the strain increases from 3.3 to 3.5; the tool wear leads to the cutting force and the increase of the temperature-strain, resulting in the residual tensile stress peaks in the circumferential and feed directions from 517MPa and 242MPa to 860MPa and 442MPa; Peak -696MPa, -356MPa increased to -756MPa, -456MPa; residual stress layer depth increased from 72μm to 85μm.