Evaluation of Material Data to the Numerical Strain‑Life Analysis of the Compressor Blade Subjected to Resonance Vibrations

This paper presents the impact of selecting the fatigue material model on the numerically determined fatigue life of a compressor blade. In the work, the first stage compressor blade of the PZL‑10W turbine engine was used. The research object contained a geometric notch with a known location and shape. In numerical studies, 8 fatigue estimation methods were used in the ε ‑N analysis (based on the Manson‑Coffin‑Basquin model). At the same time, three methods for estimating material constants associated with the cyclic hardening were employed. On the basis of the selected models, 24 sets of fatigue parameters were obtained, which were used in numerical studies. The numerical tests were carried out under resonant conditions with amplitudes of 1.5 and 1.8 mm. The numerical tests were confirmed by the experimental fatigue tests. As a result of the above‑mentioned tests, the impact of selecting the material fatigue model and hardening model on the obtained results was determined and they were referred to the initiation of the crack with the length a = 0.2 mm (achieved during experimental studies). The obtained results will constitute the basis for further fatigue tests.