The high-cycle fatigue (HCF) property and fatigue crack propagation (FCP) behavior of aircraft wheels manufactured by die forging were investigated from two sampling directions (rims and discs). The results indicate that the HCF anisotropy of the rim and disc specimens increases with decreasing stress amplitude, and the fatigue strengths are 181 MPa and 157 MPa, respectively. Based on the quantitative analysis of the fatigue fractures, a fatigue life prediction model considering the Fe/Mn-containing particles quantity factor has been established, and the predicted values are reasonably accurate to the test values. The crack path microstructure indicates that Fe/Mn-containing particles can cause crack deflection while acting as bridges for FCP; Crack closure induced by oxides and plastic zones significantly decelerated the FCP rate. Additionally, fatigue cracks tend to propagate toward grains with smaller twist angles and higher Schmid factors (SF).

中文翻译：

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2014年模锻铝合金飞机轮毂高周疲劳性能及疲劳裂纹扩展行为研究

从两个采样方向（轮缘和盘）研究了模锻制造的飞机轮毂的高周疲劳（HCF）性能和疲劳裂纹扩展（FCP）行为。结果表明，轮缘和圆盘试样的HCF各向异性随着应力幅的减小而增大，疲劳强度分别为181 MPa和157 MPa。在疲劳断口定量分析的基础上，建立了考虑Fe/Mn颗粒数量因素的疲劳寿命预测模型，预测值与试验值较为准确。裂纹路径微观结构表明，含Fe/Mn的颗粒在充当FCP桥梁的同时会引起裂纹偏转；氧化物和塑性区引起的裂纹闭合显着降低了 FCP 速率。此外，疲劳裂纹倾向于向扭转角较小和施密德因子 (SF) 较高的晶粒扩展。