| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine moving blade capable of preventing cracks generated by thermal stress due to a temperature difference between a blade and a platform when the gas turbine stops. SOLUTION: During the steady operation, cooling air 40-43 flows from cooling passages 23-26 into the moving blade 20, thereby cooling the passages 23a, 24a-24a, 25a-25c to cool the inside of the blade, and the inside of the blade is cooled to flow out to the outside. At the root part of a platform 22 of the trailing edge of the blade, a recess part 1 is provided in a circular curved surface, the curved surface of a fillet R is made large than before, or a hub hole (not shown in Fig.) for blowing off cooling air from the fillet R part to the rear edge has a larger hole area than that of the other hole. TBC is applied to the surface of the blade. By such improvement, thermal stress due to a temperature difference between the blade at the stop of the gas turbine and the platform to prevent generation of cracks.
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