OS6-10 1300℃級ガスタービン初段動翼の三次元熱応力解析にもとづく損傷評価(OS6 設備診断・運用保全技術,循環型社会における動力エネルギー技術)

抄録

All of gas turbine (GT) blades that come to the end of those lives are replaced with new ones in the scheduled inspection period. The blade is so expensive that the expansion of its life is considered as one of important subject to reduce the maintenance cost. In this study, three-dimensional thermal stress analysis and thermal fatigue damage estimation was performed for a 1300C-class GT blade under assumed operating conditions. As a result in the three-dimensional thermal stress analysis, it was revealed that the outer surface of the blade was under bi-axial compressive stress condition in start and steady state operation. Then consequently in the damage estimation, it was clarified that the middle of suction side of the blade was the most severe in terms of thermal fatigue damage and the reduction of combustion gas temperature had the effect of the reduction of damage.