APPARATUS AND METHOD FOR COOLING ROTATING BLADES IN A GAS TURBINE

摘要

56,074 An apparatus and method are provided for cooling the rotating blades in the turbine section of a gas turbine. Cooling of the leading edge is accomplished by forming a radial passageway in the leading edge portion of the blade airfoil. Rows of holes along the leading edge of the blade airfoil allow cooling air to flow from the radial passageway to the surface of the leading edge, thereby cooling the leading edge portion of the airfoil. The flow area of the radial passageway reduces as it extends radially outward so that the velocity of the cooling air flowing through the passageway is maintained. A plenum formed in the root portion of the blade distributes cooling air to small diameter holes in the center and trailing edge portion of the airfoil.