| 摘要 |
PROBLEM TO BE SOLVED: To prevent bulging generated by a pressure difference between inner pressure and outer pressure of a blade wall, in a gas turbine stationary blade in which cavities for making a cooling medium flow are formed. SOLUTION: A blade wall of a blade barrel side and a blade wall 24 of a blade back side are connected to each other by a rib 23 at a nearly front edge side from a center of a blade, two reinforcing ribs 26, 27 are radially disposed from a root part 36 of a barrel side of the rib 23 toward the blade wall 24 of the blade forward blade back side, and thereby, cavities 28, 29, 30 are dividedly disposed. Plates 25 for cooling impingement are disposed between the reinforcing ribs 26 and 27, and between the reinforcing ribs 26 and 30, and film cooling holes 31 are disposed on the blade wall 24 and the blade wall 37 of the blade barrel side where the cavities 28, 29 are formed.
|
