US Patent 8702391 Gas turbine blade

A gas turbine blade including a root and an air foil with a leading edge and a trailing edge, a cooling air channel system extending from a cooling air opening in the root via a winding serpentine channel to a trailing edge channel at the trailing edge including an air outlet at the trailing edge is provided. For efficiently cooling the trailing edge of the blade it is proposed that the cooling air channel system includes an air bypass channel connecting the cooling air opening in the root with the trailing edge channel bypassing the serpentine channel.