Analysis of Vibratory Stress and Crack Growth of Compressor Blade Under HCF Loading

The natural frequency and life of the compressor blades of the aero-engine were obtained by the modal and high cycle fatigue (HCF) experiment. Two failure criteria of compressor blades: vibratory stress and fatigue crack growth were investigated through theoretical and simulation techniques. The study found that resonant generates a non-proportional loads history output in the different regions of the compressor blade in the HCF test. The predictions of the crack growth path are compared with the experiment results. The sensitivity of vibratory stress and resonant frequency to crack locations and lengths are researched. The distribution characteristics of stress and crack should be fully understood before to make a more accurate fracture failure analysis and life predictions are verified.