US Patent 8251660 Turbine airfoil with near wall vortex cooling

A turbine airfoil having walls with radial extending near wall cooled vortex flowing channels to provide for a high cooling effectiveness with a low cooling flow requirement. A thermal skin is bonded over a main spar in which skewed ribs extend from both the spar and the thermal skin to form a vortex flowing path along the radial channels. The vortex flowing radial channels can be single pass radial channels or connected to form a 3-pass serpentine flow circuit with tip holes to discharge the cooling air from the radial channels and cool the blade tip periphery.