关键词: 涡扇发动机, 性能退化, 载荷谱修正, 叶尖间隙, 磨损, 蠕变

Abstract: 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.

Key words: Turbofan Engine, Performance Degradation, Load Spectrum Correction, Tip Clearance, Wear, Creep