In this paper, a stress analysis method and a computation program of the solution for the thermal elastic-plastic problem of turbine disk in an aeroengine are presented by incremental finite element method. That method (It is suitable to the axisymmetric disk in the gasturbine, compressor, steam turbine as well) may be used to compute the stress and displacement of turbine disk at its thermal elastic or thermal elastic-plastic stage, its cracking revolving speed and limit load capacity and what part of that enters into the plastic zone first. The method may be used to compute its loading and unloading process, its residual stress and displacement as well. It is important to analyse the strength of the turbine disk and its fracture characteristics.

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