Abstract: An experimental research on enhanced cooling of gas turbine blades are presented,based on scaled up model heat transfer tests.The air from the radial inlet channel passes through the perforated plate and is forced into the pin-finned wedged passage with a dip angle of 3°52′ and initial width 18 6mm.At a distance 9mm from the plate is located a guide pillar row with the oval cross section and then 8 pin-fin rows.