CURVED COOLING PASSAGES FOR A TURBINE COMPONENT

摘要

A turbine component having a curved cooling passage is disclosed. The turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side and a suction side extending between a leading edge and a trailing edge. An airfoil cooling circuit may be at least partially disposed within the airfoil and may be configured to direct a cooling medium through the airfoil. The curved cooling passage may generally be in flow communication with the airfoil cooling circuit such that the cooling medium flowing through the airfoil cooling circuit may be directed into the cooling passage. Additionally, the curved cooling passage may generally extend lengthwise within the airfoil between the leading and trialing edges along at least a portion of one of the pressure side and the suction side of the airfoil.