抄録
Assessment procedure of crack initiation life of a gas turbine blade based on analytical way was proposed in this study. Elastic-plastic and creep analysis was conducted using 3D FE model of the blade. It was found that axial and torsional stresses were yield on the surface of the blade and triaxil tensile stress occurs at cooling hole during operation. Crack initiation life of the blade was predicted by previously proposed life prediction method which was defined based on biaxial thermo-mechanical fatigue test results. It was concluded that the most sever portion in terms of crack initiation is mid-height of leading edge and crack initiation lives at mid-height of pressure and suction sides are three to five times longer than that of the leading edge.
