Finite element analyses were performed for varying crack tip or notch geometries and temperatures in C(T) specimens of CM247LC-DS Ni-base superalloy used in gas turbine blades to understand the accumulation of creep strains at notches. The constitutive models used considered elastic-primary-secondary creep deformation behavior. Simulations were performed under 2D plane stress, 2D plane strain, and 3D conditions for temperatures of 750°C, 850°C, and 950°C. The estimated load-line displacements as a function of time from finite element analyses and from analytical expressions were validated using results from experiments conducted on notched and fatigue precracked C(T) specimens. Differences in the development of the creep zone size due to the notch tip geometry diminish in time under plane stress conditions, but they do not for plane strain conditions. Over short periods of time, small-scale creep plays a significant role in the evolution of the notch tip creep zones. The 3D analysis results show that creep zones grow at a faster rate on the surface of the specimen than in the mid-thickness region, and these differences are exacerbated as the notch root radius decreases. This work can potentially be the basis for formulating a theory for creep crack formation from notches in CM247LC-DS alloys.