Load spectrum correction method considering performance degradation

Engine performance degradation often causes changes of performance parameters, which leads to the change of load spectrum in completing the same mission and affects 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 life prediction results and field test results. To address this problem, based on the construction of a turbofan engine model that integrates overall performance degradation and dynamic performance correction is constructed, mainly analyzing dynamic correction of engine performance by tip clearance prediction method considering wear and creep. On this basis, a load spectrum correction method for turbofan engine considering performance degradation is proposed. The engine load spectrum for the typical flight mission profile is calculated. The results show that after 3 000 cycles of engine operation, the inlet temperature of the high-pressure turbine corrected with the model proposed in this paper is 0.69% higher than that with the traditional model. Compared with the original spectrum, the corrected load spectrum has a 4.90% reduction in the high-pressure shaft speed at the maximum state, a 2.95% increase in inlet temperature of the high-pressure turbine, and a 21.05% increase in duration of the maximum state. The goal of load spectrum correction considering performance degradation is shown to be achieved.