| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine blade improved in the cooling performance of a shroud. SOLUTION: A static blade comprises a shroud part 3 having a cooling wall contacting with a combustion gas, and a blade part 5 connected to the shroud part 3. An end cooling passage 20 in which cooling vapor flows along the end of the shroud part 3 so as to cool the cooling wall is formed at the shroud part 3. A second throttle 35 which throttles the cooling vapor so as to be led to the cooling wall side is arranged at the downstream side of a second end cooling passage 20b which is inclined to the flow direction of the cooling vapor. COPYRIGHT: (C)2013,JPO&INPIT |
