Turbine blade with cooling channels for a gas turbine.

摘要

The invention relates to a turbine blade (100) for a gas turbine. The turbine blade (100) includes a platform (108), an airfoil (104) extending radially from the platform (108), and a plurality of airfoils (104) in the vicinity of an outer surface (122) of the airfoil (104). defined cooling channels (120). Each of the cooling channels (120) may include a radially inner portion (132) having a first cross-sectional area and at least one radially outer portion (134) having a second cross-sectional area, the first cross-sectional area being greater than the second cross-sectional area. The cooling channels (120) are formed as a groove in the cover layer covered by a base portion of the airfoil (104).