A finite element based model will be developed and validated to capture the evolution of residual stresses and cold work at machined features of compressor and turbine powder metallurgy superalloy disks. The focus will be to quantify, model and validate residual stress and cold work evolution at stress concentration features during simulated service in aerospace gas turbine engine disk materials. This will be accomplished by first utilizing existing NASA Test data. If the existing test data are insufficient, a minimum number of specimens will be tested if the resources permit. These specimens will have varied surface finish conditions to be determined in consultation with NASA personnel and will be tested using a thermal mechanical load history that will simulate the operating conditions of new generation of gas turbine engines and include the effect of superimposed dwell cycles. The deliverables will include effects of service history on residual stress and cold work depth profile evolutions within notches, and analytical modeling descriptions of the evolution of these parameters as a function of simulated service history. Also included will be models and algorithms extrapolating the predicted residual stresses and cold work to service conditions outside of those tested during the program.