原位拉伸研究热处理对激光选区熔化GH4169合金组织及650℃力学性能的影响OA北大核心CSTPCD
Effect of heat treatment on microstructure and mechanical properties of selective laser melting GH4169 alloy at 650 ℃ :in-situ SEM investigation
研究热处理制度对激光选区熔化成形GH4169合金组织及高温力学性能的影响.通过自主研发的SEM原位加热拉伸测试平台,探究热处理前后 650℃合金力学性能变化与动态组织演变的关系.结果表明:热处理后合金的晶粒形态由柱状晶转化为等轴晶,Laves相溶解,析出大量γ′和γ″强化相;在 650℃下,沉积态合金的屈服强度和抗拉强度分别为574 MPa和740 MPa,热处理态(HSA态)合金的屈服强度和抗拉强度分别为818 MPa和892 MPa,较沉积态分别提升了 42.5%和 20.1%;沉积态合金表面晶粒起伏更大,协调变形能力更强,塑性流动能力好;裂纹在Laves相周围萌生沿枝状晶向最大切应力方向扩展,样品颈缩后发生剪切断裂;HSA态裂纹在碳化物周围萌生沿晶界扩展,断裂方式为沿晶和穿晶相结合的混合断裂.
The effect of heat treatment on the microstructure and high temperature mechanical properties of SLM GH4169 alloy was studied by using a self-developed in-situ high temperature tensile device.The results show that the grain morphology of as-built alloy changes from columnar crystal to equiaxed crystal after homogenization+solid solution+aging treatment(HSA),coupling with Laves phase dissolution,and a large amount of γ′and γ″strengthening phase precipitates.At 650℃,the yield strength and tensile strength of the as-built sample are 574 MPa and 740 MPa,while the yield strength and tensile strength of HSA sample are 818 MPa and 892 MPa respectively,which are 42.5%and 20.1%higher than that of the deposited alloy.The deformation process can be further characterized by in-situ tensile testing.The surface grain undulation of the as-built sample gets larger,the coordinated deformation ability becomes stronger,and the plastic flow ability gets better.The cracks in the as-built sample are originated around the Laves phase,spreading along the dendrite towards the maximum shear stress,and shear fracture occurs after necking of the sample.In HSA samples,the cracks are initiated around carbides and propagating along the grain boundaries.The fracture mode is a mixed type,involving both intergranular and transgranular fractures.
朱嘉冕;吕国森;姜文祥;程晓鹏;贾泽一;吕俊霞;黄帅;张学军
北京工业大学材料与制造学部,北京 100124中国航发北京航空材料研究院,北京 100095
GH4169合金激光选区熔化高温原位拉伸热处理
GH4169 alloyselective laser meltinghigh temperature in situ tensileheat treatment
《航空材料学报》 2024 (001)
93-103 / 11
中国航空发动机集团产学研合作项目(HFZL2021CXY020);北京市自然科学基金(2232042)
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