| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine blade and a gas turbine, capable of improving the performance and enhancing the durability by effectively reducing thermal stress. SOLUTION: The gas turbine comprises a compressor 11, a combustor 12, a turbine 13 and an exhaust chamber 14. A stationary blade 21 of the turbine 13 is divided in a blade section 31, an outer shroud 32 and an inner shroud 33. The blade section 31 having a cooling passage penetrates through a through hole 32b of the outer shroud 32. The blade section 31 and the outer shroud 32 are connected to each other by fastening bolts 38 at positions where flange parts 31a, 32c thereof are in contact with each other. The blade section 31 also penetrates through a through hole 33b of the inner shroud 33 and is fastened to the inner shroud 33 by fastening bolts 40. COPYRIGHT: (C)2008,JPO&INPIT
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