| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a means capable of effectively cooling these parts at a small cooling medium flow rate, by selecting an end wall part of a gas turbine, that is, a stationary blade shroud, a moving blade platform and a divided ring, easily exposed to high temperature combustion gas and conventionally difficult for cooling. <P>SOLUTION: This cooling structure forms a large number of fine flow passages for passing a cooling medium in the vicinity of a surface of a part exposed to the high temperature of the gas turbine. A turbulent flow promoting cooling medium flow passage 5 of making the flow passage cross-sectional area different in the flow direction of the cooling medium, is formed in the vicinity of the surface of exposing the stationary blade shroud, the moving blade platform or the divided ring to the combustion gas, and an inlet opening 6a for supplying the cooling medium to the cooling medium flow passage, is arranged on a surface unexposed to the combustion gas. <P>COPYRIGHT: (C)2006,JPO&NCIPI |
