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Microstructure-Based Model for Sharp Stress Raiser-Related Fatigue Stage Length Assessment

机译：基于微观结构的急性应力提升器相关疲劳阶段长度评估模型

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摘要

A model for evaluating the fatigue life of specimens/structure elements with sharp stress raisers/defects is presented. The model permits of computing the number of cycles to fatigue crack initiation and its growth from a sharp stress raiser to failure at a constant stress span with the only application of characteristics of static strength and microstructure of the initial material. The model can be used to assess the fatigue life of components that contain structural stress raisers and defects stemming from their manufacturing technique (surface roughness, surface cuts, scratches, and microcracks). The model reliability was verified with experimental results taken from the literature, calculations appeared to be in good agreement with experimental data. Fatigue curves to a grain-size crack initiation and to fracture of smooth specimens and those with a chemically-notched blunt raiser that simulates the casting defects in aircraft components were calculated. The two sets of specimens from a Ti-6Al-4V titanium alloy differing in the cross-section (rectangular and cylindrical) and in microstructure (different grain sizes). Smooth specimens exhibited the test surface roughness R-v = 10 and 19 mu m (average dent depth), which was assumed to be a sharp raiser for calculations. The model need not long-term and labor-consuming high-cycle fatigue tests to construct the fatigue curve.
机译：提出了一种评价试样/结构元件的疲劳寿命的模型，具有急剧应力提升器/缺陷。计算疲劳裂纹启动的循环次数的模型允许与急性应力延伸器发生故障的循环次数及其生长，持续应力跨度的静态应力跨度的峰值跨度的唯一应用和初始材料的微观结构的应用。该模型可用于评估含有结构应力提升器的部件的疲劳寿命和源自其制造技术（表面粗糙度，表面切割，划痕和微裂纹）。通过从文献中取出的实验结果，验证了模型可靠性，似乎与实验数据吻合良好。疲劳曲线曲线对晶粒尺寸的裂纹起始和平滑样品的断裂，并计算出拟模拟的钝齿轮，用于模拟飞机组分中的铸造缺陷。来自Ti-6AL-4V钛合金的两组标本在横截面（矩形和圆柱形）和微观结构（不同粒度）中不同的钛合金。平滑样本表现出测试表面粗糙度R-V = 10和19μm（平均凹陷深度），这被假设是用于计算的尖锐提升剂。该模型不需要长期和劳动消耗的高循环疲劳试验，以构建疲劳曲线。

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