Patent ID: 6874988

Claim:
A gas turbine blade, comprising: an airfoil leading edge; an airfoil trailing edge; and an inner cooling structure including a meandering cooling passage with sections directed along a blade axis of the gas turbine blade, for directing a cooling fluid from the airfoil leading edge to the airfoil trailing edge, wherein a first section of the sections runs along the airfoil leading edge and includes an inlet region for the cooling fluid and an outlet region for the cooling fluid, the first section further including an impingement-cooling insert, which, with its insert front side which is directed toward the airfoil leading edge, runs parallel to the airfoil leading edge, the impingement-cooling insert tapering toward the outlet region, such that, in the first section, the type of cooling of the flowing cooling fluid in the first section changes from impingement cooling to convective cooling; wherein the gas turbine blade is designed as a guide blade including an inner ring, the inner ring, when the guide blade is fitted into a gas turbine, sealing off a hot-gas duct of the gas turbine relative to a rotor of the gas turbine, and including an inner-ring cooling passage leading from the impingement-cooling insert to the inner ring.