| 摘要 |
<p>A cooled blade (10) for a gas turbine comprises an airfoil (11) extending in radial direction of the turbine or longitudinal direction of the blade (10), respectively, between a platform (12) and a blade tip (14), said airfoil (11) being bordered across the airfoil (11) by a leading edge (15) and a trailing edge (16), and having a suction side (17) and a pressure side (18), whereby at the trailing edge (16) a first cooling passage (25) runs parallel to the trailing edge (16) from the platform (12) to the blade tip (14) in the interior of the airfoil (11), which cooling passage (25) is supplied with a cooling air flow (21 ) from the platform side, and from which cooling air is discharged through a plurality of cooling holes (19, 20a, 22, 23) arranged all over the blade (10). For such a blade the cooling is optimized by providing a first cooling passage (25), the passage area of which is tapered in radial direction by between 35% and 59%.</p> |
