A gas turbine engine component comprising: a platform and an airfoil extending radially from the platform relative to an axis of rotation of a turbine that will receive the component; at least one central cooling channel extending in said airfoil, said airfoil having a thickness measured between a concave wall and a convex wall, with said at least one central cooling channel being formed between said concave and said convex walls (69, 71), and a plurality of inlets radially spaced along the airfoil, characterized in that each of said plurality of inlets is for communicating cooling air from said at least one central cooling channel to a radially extending sub-channel, wherein said radially extending sub-channels provides a microcircuit having a relatively thin thickness in a direction defined between said central cooling channel and one of said concave and convex walls (69, 71) of the airfoil, and wherein cooling air passes into said inlet, and toward one of said walls (69, 71), each said inlet communicating with a first 90° bend into a communication channel which extends generally axially, said first 90° bend extending into a direction generally parallel with said wall (69, 71), and into a second 90° bend, said second 90° bend turning said communication channel into said radially extending sub-channel and radially through the airfoil, and each of the plurality of radially extending sub-channels sharing an intermediate wall with an adjacent sub-channel and extending along a direction having a major component in a radial direction of the airfoil, said radially extending sub-channels being axially spaced. a platform and an airfoil extending radially from the platform relative to an axis of rotation of a turbine that will receive the component; at least one central cooling channel extending in said airfoil, said airfoil having a thickness measured between a concave wall and a convex wall, with said at least one central cooling channel being formed between said concave and said convex walls (69, 71), and a plurality of inlets radially spaced along the airfoil, characterized in that each of said plurality of inlets is for communicating cooling air from said at least one central cooling channel to a radially extending sub-channel, wherein said radially extending sub-channels provides a microcircuit having a relatively thin thickness in a direction defined between said central cooling channel and one of said concave and convex walls (69, 71) of the airfoil, and wherein cooling air passes into said inlet, and toward one of said walls (69, 71), each said inlet communicating with a first 90° bend into a communication channel which extends generally axially, said first 90° bend extending into a direction generally parallel with said wall (69, 71), and into a second 90° bend, said second 90° bend turning said communication channel into said radially extending sub-channel and radially through the airfoil, and each of the plurality of radially extending sub-channels sharing an intermediate wall with an adjacent sub-channel and extending along a direction having a major component in a radial direction of the airfoil, said radially extending sub-channels being axially spaced.