Characterizations of fatigue crackSpropagationSresistance of the key bearing structures precisely in aviation area are the basis of its service lifetime evaluation. In this work, Ti-2Al-1.5Mn titanium alloy was selected, some CT samples were prepared along different sheet orientation, the fatigue crack growth rate test was carried out, the stress intensity factor range DK at different crack stage were calculated based on full-field measurements and traditional method. It can be concluded that the fatigue crack growth rate da/dN versus DK curve and crack growth path are affected by material orientation. Compared with the traditional method, DK calculation based on full-field measurements was proved to be more efficient. For one thing, the crack shielding effect due to plastic zone in crack tip can be directly considered. For another, a more accurate DK can be got for the case that the crack path was zigzag. It has a wideSapplication in future of DK calculation based on full-field measurements.