Turbine blade

A blade for a gas turbine engine having a turbine rotor disk, the blade comprising:

• a dovetail having at least one cooling air inlet passage and configured to mount to the turbine rotor disk;
• an airfoil extending radially from the dovetail and having an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a root and a tip, with the root being adjacent the dovetail;
• and
• a leading edge cooling circuit located within the airfoil adjacent the leading edge and comprising:
• a supply passage extending from the root toward the tip and fluidly coupled to the cooling air inlet passage at the root,
• a pin bank passage in fluid communication with the supply passage and extending between the root and the tip, with a plurality of pins located within the pin bank passage, and
• at least first and second cooling passages fluidly coupled to the pin bank passage and arranged on opposite sides of the pin bank passage;
• wherein the pin bank passage, and first and second cooling passages define a near surface cooling zone and are located between the supply passage and the outer surface adjacent the outer surface, and cooling air from the cooling air inlet passage travels through the supply passage in a first radial direction from root-to-tip, returns through the pin bank in a second radial direction, opposite the first radial direction, and then flows through the first and second cooling passages in the first radial direction.