| 摘要 |
<p>The invention refers to a blade (10) for a gas turbine, comprising a blade airfoil (11), the blade wall (18) of which encloses an interior space (17), wherein, for cooling the blade wall (18), provision is made in said blade wall (18) for a cooling arrangement (19) which has a radial passage (20) extending in the longitudinal direction of the blade and from which a multiplicity of cooling passages (21, 22), extending in the blade wall (18), branch in the transverse direction, and from which a multiplicity of film-cooling holes (23) are led to the outside in the transverse direction. Particularly efficient cooling is made possible by the distribution of the film-cooling holes (23) along the radial passage (20) being selected independently of the distribution of the cooling passages (21, 22) along the radial passage (20).</p> |
