| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine stationary blade segment, having a stronger cooling design which has the number of insets reduced. while reducing costs and complexity for casting. SOLUTION: This stationary blade is provided with cavities 34, 36, 38, 40 and 42 for allowing a cooling medium to flow. The cooling medium enters an outer chamber of an outer wall, passes through an impingement plate 60, impingement-cools an outer band wall for partially defining a high-temperature gas path, and flows inward in the radial direction through openings 64, 66 and 68 of first, second and fourth cavities to cool the stationary blade. The spent cooling medium flows into an inner chamber of an inner wall and then flows outward in the radial direction through an impingement plate 84 to cool the inner wall. The spent cooling medium passes through the third cavity 38 and is discharged from the turbine stationary blade segment from the outside wall. Inserts 70, 72 and 74, having impingement openings for impingement-cooling for the stationary blade wall, are provided in the first, second and third cavities. The fifth cavity 42 provides air cooling for the rear edge.
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