| 摘要 |
PROBLEM TO BE SOLVED: To enable a gas turbine to cope with a high temperature by applying an air cooling for a range which can be coped with the air cooling and applying a vapor cooling for a range which is difficult to cope with the air cooling. SOLUTION: There are provided in a stationary blade 1, a serpentine flow channel 3 through which vapor for cooling is passed through and an air flow channel 10 disposed separately from the serpentine channel 3 but adjacent to the back end section thereof. Also, there are provided a flow channel for air cooling arranged at the outer edge section and cooling sections by the vapor impingement and air impingement inside thereof in a shroud 4. In an inner shroud 11, there are provided a flow channel for air cooling arranged at the outer edge section and shaped holes inside thereof. Air coming out from the shaped holes acts as a film cooling.
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