This paper deals with the strength analysis for turbine disk of aeroengine. A finite element analysis program of thermoelastoplastic creep is formulated

which imitates a cyclic loading in flight. Considering the influence of factors of creep

change of material's properties

and process of temperature elevation

the stress analysis of the disk-body is accomplished under various working conditions. Moreover

the residual stress resulting from a cyclic loading is calculated. Some useful conclusions have been drawn for engineering design.