Abstract: 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.