| 摘要 |
PROBLEM TO BE SOLVED: To provide a cooling turbine aerofoil for improving cooling performance of a nozzle rear edge part. SOLUTION: This aerofoil has an array of partition walls 122, 222 separating in the radial direction, extending in the longitudinal direction and determining a plurality of cooling channels 124, an aft pin 126 and an elongated turbulator 128 arranged in at least one of the cooling channels 124, lands 134 mutually separating in the radial direction and extending in the longitudinal direction, and an array of dividers 136 extending in the longitudinal direction. The turbulator is arranged at a predetermined angle to a shaft in the longitudinal direction of a nozzle blade so that an aft end 148 of the turbulator approaches more than a turbulator forward end 146 to the partition walls. The lands and the separating members regulate a plurality of trailing edge slots 138 between these members, and the respective trailing edge slots 138 have an inlet 140 communicating with a trailing edge cavity 114 and a shaft directional downstream side outlet communicating with a trailing edge 150 of the nozzle blade. COPYRIGHT: (C)2007,JPO&INPIT
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