发动机性能退化往往引起性能参数发生改变，进而导致完成相同飞行任务时载荷谱发生变化，对发动机结构寿命预测造成影响。目前，整机寿命试车载荷谱编制过程中尚未考虑性能退化因素影响，导致寿命试车结果与外场存在较大误差。针对这一问题，构建了综合整机性能退化与动态性能修正的涡扇发动机模型，重点研究了考虑磨损、蠕变的叶尖间隙预测方法对发动机性能的动态修正，提出了一种考虑性能退化的涡扇发动机载荷谱修正方法。同时对典型飞行任务剖面下的载荷谱进行了计算，结果表明：发动机在运行3000循环后，动态性能修正模型的高压涡轮进口温度较传统模型升高0.69%；修正后的载荷谱与原谱相比，其最大状态的高压轴转速降低4.90%、高压涡轮进口温度上升2.95%，最大状态持续时间增加21.05%，实现了考虑性能退化的载荷谱修正目标。
The performance degradation of the engine often causes the change of the performance parameters, which leads to the change of the load spectrum to complete the same mission, and affects the life prediction of the engine structure. At present, the above factors have not been considered in the process of compiling the load spectrum of the whole machine life test, resulting in a large error between the life test results and the external field. Aiming at this problem, based on the construction of a turbofan engine model that integrates overall performance degradation and dynamic performance correction, a load spectrum correction method for turbofan engine con-sidering performance degradation is proposed. Among them, the dynamic correction of engine performance by tip clearance predic-tion method considering wear and creep was mainly studied. At the same time, the engine load spectrum under typical flight mission profile was calculated. The results show that after 3000 cycles of engine operation, the inlet temperature of the high-pressure turbine of the dynamic performance correction model in this paper is 0.69 % higher than that of the traditional model. Compared with the original spectrum, the corrected load spectrum has a 4.90 % reduction in the maximum state of the high-pressure shaft speed, a 2.95 % increase in the high-pressure turbine inlet temperature, and a 21.05 % increase in the maximum state duration. The goal of load spectrum correction considering performance degradation was achieved.
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