| 摘要 |
In gas turbine second stage stationary blade, cooling air passage of inner shroud is improved so as to obtain enhanced cooling efficiency. In inner shroud 126, there are provided leading edge passage 42 and trailing edge passage 44, both extending from blade portion and mutually separated by rib 40, and impingement plates 83, 84 having multiplicity of small holes 101. Opening portion 68 between the blade portion and the inner shroud 126 is closed by bottom plate 150 and, together with recess portion 100 at bottom portion of the leading edge passage 42, connects to passage 188 of leading edge portion 41 via passage 90'. Air from the trailing edge passage 44 flows into cavity 45 to be injected through the small holes 101 of the impingement plates 83, 84 for cooling of central portion of the inner shroud 126 and then is discharged as air 60 through passages 92 of the trailing edge portion 43. Entire amount of the air from the leading edge passage 42 enters the passage 188 to be enhanced of heat transfer effect by turbulators 200 and further flows separatedly into passages 93, 94 of side edge portions for cooling therearound to be then discharged as air 61. Air amount in the leading edge portion 41 and the side edge portions are increased and cooling effect is enhanced. <IMAGE> <IMAGE> |
