Turbine blade with improved trailing edge cooling

A turbine blade including an airfoil section, a root section, and a platform section between the airfoil section and the root section, wherein an exterior surface of said turbine blade is exposed to a hot combustion gas above a flow path line, said turbine blade comprising:

• a trailing edge pin bank cooling channel in the airfoil section;
• a cooling air supply channel in the root section;
• a channel interconnecting the cooling air supply channel to the trailing edge pin bank cooling channel, said channel having a radius of curvature to extend the channel from the cooling air supply channel in the root section, across the flow path line and to the trailing edge pin bank cooling channel in the airfoil section.

A turbine blade including an airfoil section, a root section and a platform section between the airfoil section and the root section, said turbine blade comprising:

• a trailing edge pin bank cooling channel in the airfoil section;
• wherein said airfoil section extends in a radial direction from an inner diameter region attached to the platform section, to an outer diameter region;
• and wherein a width of the trailing edge pin bank cooling channel at the inner diameter region and at the outer diameter region is less than the width of the trailing edge pin bank cooling channel at an intermediate region positioned between the inner diameter region and the outer diameter region.