Improving turbine disk geometries from INCONEL718 leads to emission reductions of future engines. To that purpose, the residual stress fields from the manufacturing process must be taken into account in the design. The manufacturing process consists of forging, heat treatment and machining to the final contour. The entire process comprises a temperature range of about 1000 °C, in which precipitates nucleate and growth. A thermo-kinetic model was parameterized and validated on the basis of extensive experimental investigations. A semi-empirical creep law was derived which considers the influence of precipitation strengthening on secondary creep rates. Using the microstructural based constitutive model and an accurate temperature field simulation, the residual stresses could be simulated with an accuracy of ± 50 MPa. Validation was carried out using the hole drilling technique and neutron diffraction. The integration of the improved model into the design process of turbine disks enables consideration of the manufacturing process and thus of the residual stresses.