| 摘要 |
PROBLEM TO BE SOLVED: To reduce the likelihood of the generation of cracks in a rear edge region of the root of a blade in an aero foil section, by reducing thermal stress and mechanical stress generated by inconformity of the aerofoil section with a shank portion. SOLUTION: The gas turbine moving blade has a platform 38 in which a groove 46 is cut out. The groove portion 46 extends from a recess side to a rear edge side of the platform, and the groove portion gets out from the rear edge. The depth of the groove portion 46 is not to be out of a line of stress 70. Therefore, the groove portion 46 changes a loading path to be in a direction spaced from the end edge. Even in a transient operation, in addition to a stationary state, a full speed operation, and a full load operation, the high thermal stress and mechanical stress that are generated at a connecting portion of the rear edge of the gas turbine air cooled moving blade and the platform are reduced by the position and the depth of the groove portion.
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