| 摘要 |
<p>Gas turbine cooled stationary blade is improved in the structure of a blade and outer and inner shrouds to enhance cooling efficiency and to prevent occurrence of cracks due to thermal stresses. Blade (1) wall thickness between 75% and 100% of blade height of a blade leading edge portion is made thicker and blade (1) wall thickness of other portions is made thinner, as compared with a conventional case. Protruding ribs (4) are provided on a blade (1) convex side inner wall between 0% and 100% of the blade height. Blade (1) trailing edge opening portion is made thinner than the conventional case. Outer shroud (2) is provided with cooling passages (5a, 5b) for air flow in the shroud both side end portions. Inner shroud (3) is provided with cooling passages (9a, 9b) for air flow and cooling holes (13a, 13b) for air blow in the shroud both side end portions. By the blade (1) structure and the shroud (2, 3) cooling passages (5a, 5b, 9a, 9b) and cooling holes (13a, 13b), cooling effect is enhanced and cracks are prevented from occurring. <IMAGE></p> |
