| 摘要 |
Described is a cooling device for a shroud (1) of a gas turbine blade, having a cooling channel system provided in the shroud (1), which is provided radially to the gas turbine blade with cooling channels (4) that are open on one side, and which is closed off with a cover plate (2), The invention is characterized in that, between the cover plate (2) and the cooling channels (4) that are open on one side, an impact cooling plate (5) is provided in such a way that the impact cooling plate (5) rests on the cooling channels (4) that are open on one side, is pressed against them by force, and encloses a space with the cover plate (2).
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