The calculations and tests of stress distributions for load-bearing case of aeroengine are presented. It is noted that the stress finite element analysis of the case may be divided into three steps

namely model evaluation

stress distribution calculation of the actual case and detailed calculation of partial structures. The basic approach and major achievements of the theoretical and experimental researches on thermal stresses in cylindrical case are described. Finally

the progress in the low-cycle fatigue life

prediction of notched members at room and elevated temperatures

and the essential feactures of the finite element analysis program for elastoplastic creep are briefed.