Abstract Elevated fatigue behaviors of resin matrix composites are considerable key to the application of aeroengine that requires fatigue resistance at elevated temperature. However, undeniably, very few studies are focused on this issue, thereby resulting in limitation applications of resin matrix composites in aeroengine components, i.e. blades and case. In this work, the fatigue responses of layer-to-layer 3D angle-interlock woven composites (2.5DWC) were experimentally and numerically studied at room and elevated temperatures. Experimental results show that the weft direction fatigue lives at 20 °C and 180 °C experienced a relatively short cycle (less than 104 cycles) prior to the failure. But, once the stress level declined to a threshold value (dropped by 1–2%), the fatigue limitation would be activated, regardless of temperature. Moreover, the residual strength at 20 °C or 180 °C was reinforced compared to the static strength. Considering the fatigue data and fracture morphology, probable damage mechanisms corresponding to temperature-dependent weft direction fatigue behaviors of 2.5DWC were proposed. A temperature-dependent fatigue life prediction model of 2.5DWC was proposed, based on which the weft direction fatigue lives, damage propagation processes and residual stiffnesses of 2.5DWC at 20 °C and 180 °C were predicted.

中文翻译：

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室温和高温下层对层 3D 角互锁编织复合材料的纬向拉-拉疲劳响应

摘要 树脂基复合材料的高疲劳行为是航空发动机在高温下具有抗疲劳性能的关键。然而，不可否认的是，很少有研究关注这个问题，从而限制了树脂基复合材料在航空发动机部件中的应用，即叶片和外壳。在这项工作中，层对层 3D 角互锁编织复合材料 (2.5DWC) 的疲劳响应在室温和高温下进行了实验和数值研究。实验结果表明，纬向疲劳寿命在 20°C 和 180°C 下经历了一个相对较短的循环（小于 104 个循环），然后失效。但是，一旦应力水平下降到阈值（下降 1-2%），无论温度如何，疲劳限制都会被激活。而且，与静态强度相比，在 20 °C 或 180 °C 下的残余强度得到了增强。结合疲劳数据和断裂形态，提出了2.5DWC随温度变化的纬向疲劳行为对应的可能损伤机制。提出了2.5DWC随温度变化的疲劳寿命预测模型，据此预测了2.5DWC在20℃和180℃下的纬向疲劳寿命、损伤传播过程和残余刚度。