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SLM增材制造钛合金BCC超结构压缩疲劳断裂行为

徐瑞阳,孙文博,段旭朝,马玉娥   

  1. 西北工业大学
  • 收稿日期:2025-07-11 修回日期:2025-08-22 出版日期:2025-08-28 发布日期:2025-08-28
  • 通讯作者: 马玉娥
  • 基金资助:
    航空发动机用增材制造钛合金的高温疲劳和蠕变断裂行为及其失效机理

Fatigue Fracture Behavior of SLM Additively Manufactured Titanium Alloy BCC Super-Structures under Compressive Loading

1,Wen-Bo SUN1,Xu-Zhao DUAN1,Yu E Ma   

  • Received:2025-07-11 Revised:2025-08-22 Online:2025-08-28 Published:2025-08-28
  • Contact: Yu E Ma

摘要: 增材制造超结构以其优秀的减重性能及可设计性,满足了航空航天飞行器高性能轻质一体化的要求。然而增材制造产生的表面粗糙度和内部孔隙易使疲劳裂纹萌生,导致超结构提前失效。为研究表面粗糙度和孔隙对疲劳性能的影响机理,设计了增材制造BCC超结构试件,完成了五种载荷工况下的超结构疲劳试验,获取了其S-N曲线。基于半经验公式计算表面粗糙度引入应力集中系数,结合有效承载面积参数修正孔隙及表面粗糙度的影响。通过三维重建模型的有限元仿真并验证其准确性后,代入Neuber-Kuhn公式求得了疲劳极限。在有效承载面积修正的研究基础上,建立了单杆的疲劳S-N曲线,构建了从单杆S-N到超结构S-N的映射方法,给出了修正的S-N曲线。结果表明:有效承载面积修正后的模型能更好反映表面粗糙及内部孔隙的耦合影响,从而提高超结构的疲劳极限和寿命的预测精度;单胞模型的周期性边界条件可以有效模拟整体结构的应力集中;采用修正的S-N曲线预测超结构疲劳寿命,其结果在三倍分散带以内。

关键词: 增材制造, 超结构, 表面粗糙度, 孔隙, 疲劳寿命

Abstract: Additively manufactured lattice structures are highly promising for aerospace vehicles due to their excellent weight reduction performance and design flexibility, fulfilling the demand for high-performance, lightweight, and integrated components. However, surface roughness and internal porosity introduced by additive manufacturing tend to serve as initiation sites for fatigue cracks, potentially leading to premature failure of the lattice structures. To investigate effects of surface roughness and porosity on fatigue performance, BCC lattice specimens were designed and fabricated by additive manufacturing. Fatigue tests under five different loading levels were conducted to obtain the corresponding S-N curves. A semi-empirical formula was used to calculate the stress concentration factor introduced by surface roughness. Additionally, the concept of effective load-bearing area was applied to account for the influence of both porosity and surface roughness. The accuracy of this method was verified through finite element simulations based on 3D reconstructed models, and the Neuber-Kuhn formula was used to estimate the fatigue limit. Based on the effective area correction, a fatigue S-N curve for a single strut was established, then a mapping method from the single-strut S-N curve to the lattice S-N curve was developed, and a corrected S-N curve was proposed. It is shown that the model incorporating effective load-bearing area correction more accurately reflects the coupled effect of surface roughness and internal porosity, thereby it can improve the predictive accuracy of the fatigue limit and fatigue life of the lattice structures. The periodic boundary conditions in one unit lattice can be built and effectively simulate stress concentration in the whole structure. The corrected S-N curve is used to predict the fatigue life of the lattice, and its results fall within a scatter band of factor 3.

Key words: Additive Manufacturing, Superstructure, Surface Roughness, Pore, Fatigue Life

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