| 摘要 |
The present invention relates to a rotating blade (5), in particular for a compressor or turbine stage of a gas turbine, having a radially outer rib arrangement with at least one rib (2), onto which a coating (3) is disposed, whereby, in a meridian section (FIGS. 2, 3, 4), the coating (3) has an outer contour (3.1), which extends axially outwardly in the radial direction.
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