Abstract: A coolable airfoil 16 for a rotary machine is disclosed. The coolable airfoil includes a plurality of cooling passages 56, 86, 88 and 114 extending in the spanwise direction. A plurality of turning passages such as the turning passage 82 and the turning passage 90 turn the flow between the spanwisely extending passages. A vane 92 in the turning passage 90 is spaced from a spanwisely extending baffle 48 to form a sub-passage 94 therebetween upstream of a corner region 90c. A trip strip 96 extends between the vane and the wall and is angled with respect to the approaching flow. A similar construction is found in the turning passage 82. In one particular embodiment, the turbine blade includes a spanwisely extending leading edge passage connected to the trailing edge region by a chord-wisely extending tip passage 58.