Patent ID: 8251660

Claim:
A turbine airfoil for a gas turbine engine comprising: a main spar having a cross sectional shape of an airfoil with a pressure side wall and a suction side wall, and a leading edge and a trailing edge; a hollow cavity formed within the main spar; a thermal skin secured onto the main spar to form an airfoil surface and to form a plurality of radial extending near wall cooling passages; a first series of skewed ribs extending from the main spar and into the radial extending near wall cooling passage; a second series of skewed ribs extending from the thermal skin and into the radial extending near wall cooling passage; the first and second series of skewed ribs both being half-moon shaped pieces that form a spiral flow path; and, the first series of skewed ribs extend into a space formed between the second series of skewed ribs to form a vortex generating flow path for cooling air flowing through the radial extending near wall cooling passages.