Patent ID: 7556476
Filing Date: 2009-07-07
Classification: F01D,F05D

Abstract:
1. A turbine airfoil used in a gas turbine engine, the airfoil comprising: an airfoil main body having a shape of an airfoil with a pressure side and a suction side, and a leading edge and a trailing edge; a forward cooling air supply channel formed within the airfoil main body; a mid-chord cooling supply channel formed within the airfoil main body; a spent air collector cavity formed within the airfoil main body and positioned between the forward and mid-chord cooling supply channels; a first pressure side impingement channel in fluid communication with at least the forward cooling air supply channel and the spent air collector channel; a first suction side impingement channel in fluid communication with the mid-chord cooling air supply channel and the spent air collector channel; and, a first suction side film cooling hole in fluid communication with the spent air collector channel.