| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for convection-cooling the mating surfaces of side walls between the seal slot and hot gas flow passage of a turbine nozzle segment. SOLUTION: In an example embodiment, a turbine nozzle 40 comprises an outer band portion 42, an inner band portion 44, at least one nozzle vane 46 extending between the inner band portion and the outer band portion, and at least one cooling channel 80 at least partially passed through at least one of the outer band portion and the inner band portion and extending in the axial direction. At least one nozzle vane, the inner band portion, and the outer band portion form a flow passage 72 for making hot combustion gas flow therein. Each cooling channel includes at least one inlet 82 separated from the flowing hot combustion gas. COPYRIGHT: (C)2005,JPO&NCIPI
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