| 摘要 |
The invention relates to a turbine blade (1) with an internally cooled turbine blade airfoil (3), in which a hollow space (10) is divided by rib elements (11, 12) in at least one cooling channel (13) carrying a coolant (14), wherein a recess of material (29), which is arranged next to at least one rib element (11, 12) on a turbine blade airfoil wall (5), is embodied such that tensions occurring within the turbine blade airfoil (3) can be reduced in a region (28) surrounding the at least one rib element (11, 12). |
