| 摘要 |
This invention relates to a tip shroud for a moving blade to be used at a downstream stage of a gas turbine. The tip shroud is elongated in its creep lifetime by feeding it effectively with cooling air. In the tip shroud 11, there are cut-off portions 12 and 13 which are passed by a hot combustion gas so that they are influenced by a thermal stress and liable to have a creep. On the shroud faces, there are formed grooves 31 and 32, and 33 and 34, and cooling guide covers 21 and 22. Cooling guide covers 21 and 22 are closed at their one side with members 21a and 22a and opened at their other end to cover the air holes 17 so that the cooling air is fed to cool the cut-off portions 12 and 13 individually. The metal temperature rise in the cut-off portions 12 and 13, as will be influenced by the hot combustion gas, can be suppressed to elongate the creep lifetime of the tip shroud. <IMAGE> <IMAGE> |
