NOVELTY - The airfoil has a pressure side wall and a suction side wall extending between a leading edge (11) and trailing edge (12). Multiple pass serpentine flow cooling circuits extend along a side wall of the airfoil. A set of pin fins (41) extends across each of the channels (21-27) of multiple pass serpentine flow cooling circuits. The pin fins are perpendicular to a surface of the airfoil wall. A TBC is applied over the outer airfoil wall, and is formed as a single piece with the outer airfoil wall from a metal printing process.    USE - Air cooled turbine airfoil for use in rotor blade (claimed) utilized in gas turbine engine.    ADVANTAGE - The airfoil provides an counter flow cooling technique utilized for the airfoil suction surface to maximize the use of cooling air, so that the cooler cooling air is supplied at down stream of the airfoil suction surface, where the airfoil heat load is high, and cooling air flows toward the airfoil leading edge, picking up heat along the pin fins channel, and counter flow cooling mechanism maximizes the use of cooling air, thus providing high overall cooling efficiency for the airfoil suction side surface. The pin fins utilizes in the suction side serpentine flow channel conducting heat from the airfoil wall into the inner partition wall, and pressure side and suction side pin fins are connected to the inner partition wall, so as to conduct heat to each other while the cooler cooling air cavity on the pressure side corresponds to the warmer air cavity on the suction side and balancing the wall temperature for the airfoil pressure and suction side walls, thus achieving thermally balanced blade cooling design. The airfoil provides an thermally balanced cooling design and an cooling circuit is designed to maximize the use of the hot gas side pressure distribution, so that the cooling flow initiates at the airfoil leading edge and ends at the airfoil suction side just downstream from the leading edge, which lowers the required cooling supply pressure, thus reducing the overall blade leakage flow in an effective manner.    DESCRIPTION OF DRAWING(S) - The drawing shows a cross sectional view of near wall serpentine flow cooling circuit.    Blade (10)    Leading edge (11)    Trailing edge (12)    Channel/leg (21-27)    Film cooling holes (31, 33, 34)    Cooling air exit holes (32)    Pin fins (41)    Trip strips (42)