Cooled blade for a gas turbine

A blade for a gas turbine, comprising:

• an airfoil section extending in a radial direction of the turbine or in a longitudinal direction of the blade between a platform and a blade tip, the blade tip being provided with a cap, the airfoil section being bounded transversely with respect to the longitudinal direction by a leading edge and a trailing edge and having a pressure face and a suction face;
• cooling channels extending substantially in a radial direction between the platform and the blade tip in an interior of the airfoil section, for receiving a cooling medium flow,
• first cooling holes for convection cooling provided on the pressure face of the blade;
• and
• second cooling holes for film cooling provided on the suction face of the blade, the first and second cooling holes being arranged in an area of the blade tip and operatively connected to the cooling channels and distributed over the blade width, the cooling medium being passed to an exterior of the area of the cap and/or through the cap of the blade.