| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine blade of a gas turbine. SOLUTION: Blade walls 14, 16 are divided into sections of locally adapted material temperatures, based on the present invention. The low material temperature exists in a portion with a support rib 24 moved to the blade wall, in the wall blade. The portion of high material temperature exists in a portion with a cavity 31 arranged in an inside of the blade wall, in the wall blade. This is attained by coated layers 32, in particular, a ceramic insulating layer, of different coated layer thicknesses allowing the different material temperatures in the blade wall. In particular, a portion B of a hydraulic medium side surface 30 of the blade wall positioned in a side opposite to the support rib integrally formed in an inside 22 has an insulating layer thicker than a portion A of the surface 30 of the blade wall cooled by a coolant flowing in the cavity 31. The material temperature is uniformized in a coupling portion 26 by this manner, and a life of the turbine blade is prolonged thereby. COPYRIGHT: (C)2008,JPO&INPIT
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