| 摘要 |
PROBLEM TO BE SOLVED: To impingement-cool an undercut area of a nozzle band for a gas turbine. SOLUTION: A nozzle segment 10 for a gas turbine has an outside and an inside bands 12, 14. Each band includes a side wall 40, a cover 20, and an impingement plate 22 positioned between the cover and a nozzle wall 18 so as to define a cavity between them into two. The cooling steam is supplied to one cavity 24, and made to flow through openings 30 of the impingement plate 22 so as to cool the nozzle wall 18. A side wall 40 of the band and an inside-facing flange 42 define an undercut area 44 with the nozzle wall. The inside-facing flange has plural openings 56 for directing the cooling steam for cooling the side wall provided between the nozzle segments adjacent to each other.
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