Turbine blade having a row of spanwise nearwall serpentine cooling circuits

摘要

A turbine blade with an array of cells arranged along the pressure side and suction side of the airfoil to provide near wall cooling to a thin thermal skin that forms the airfoil surface of the airfoil. The blade includes a main spar that forms the support for the thin thermal skin and includes a number of cooling air supply cavities and cooling air discharge cavities formed in an alternating manner along the chordwise length of the airfoil. A row of cells extend along the spanwise direction of the airfoil and includes a mini serpentine flow passage with an inlet hole connected to the adjacent supply cavity and a discharge hole connected to the adjacent collector cavity. The cooling air flow and pressure can be controlled for each of the cells by sizing the metering inlet hole to control the metal temperature of the airfoil as selected locations.