Rotor components of an aircraft engine in service are usually subjected to combined high and low cycle fatigue (CCF) loadings. In this work, combining with the load spectrum of CCF, a modified damage accumulation model for CCF life prediction of turbine blades is first put forward to take into account the effects of load consequence and load interaction caused by high‐cycle fatigue (HCF) loads and low‐cycle fatigue (LCF) loads under CCF loading conditions. The predicted results demonstrate that the proposed model presents a higher prediction accuracy than Miner, Manson‐Halford model does. Moreover, to evaluate the fatigue reliability of rotor components, reliability model with the failure mode of CCF is proposed on the basis of the stress‐strength interference method when considering the strength degeneration, and its results show that the reliability model with CCF is more suitable for aero‐engine components than that with the failure mode of single fatigue.

中文翻译：

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用于联合循环载荷下发动机部件可靠性分析的疲劳损伤累积模型

使用中的飞机发动机的转子组件通常承受高循环疲劳和低循环疲劳（CCF）的共同载荷。在这项工作中，结合CCF的载荷谱，首先提出了一种改进的涡轮叶片CCF寿命预测损伤累积模型，以考虑到载荷后果和高周疲劳（HCF）载荷引起的载荷相互作用的影响CCF负载条件下的低周疲劳（LCF）负载。预测结果表明，提出的模型比Miner，Manson-Halford模型具有更高的预测准确性。此外，为了评估转子部件的疲劳可靠性，在考虑强度退化的情况下，基于应力-强度干涉法，提出了带有CCF失效模式的可靠性模型，