| 摘要 |
The present invention relates to a gas turbine blade (1) with a closed steam cooling system. A partition (37) that is, in particular, of sheet metal divides a first partia l cavity (23) in an axial direction so that steam can flow from the first secondary chamber (31) into a leading edge cavity (21) so as to cool this by impingement, and from this into a second secondar y chamber (33). This entails the advantage of a configuration for a closed steam cooling system that is cost effective and particularly simple from the standpoint of production techniqu e, and at the same time ensures a leading edge (11) that is of an aerodynamically efficient shape.
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