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 to 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 used. Based on the selected models, 24 sets of fatigue parameters were obtained, which were used in numerical studies. Numerical tests were carried out in resonant conditions with amplitudes of 1.5 and 1.8 mm. Numerical tests have been confirmed by 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). Obtained results will be the basis for further fatigue tests.