Fatigue life analysis of an aero-engine with the measured load spectrum

摘要

According to the aero-engines' flight hours and the speed cycle number, we can obtain the relationship between the load spectrum and the life of its main components; According to the analysis of actual measured load spectrum and the fatigue damage model, this paper adopts the S-N curve and Miner's rule to estimate the fatigue life of engine's first stage turbine disk.