Patent ID: 6499949
Filing Date: 2002-12-31
Classification: F01D,F05D,Y02T,Y10T

Abstract:
A cooling system for actively cooling a flow path surface region of a gas turbine airfoil trailing edge extending into a gas flow path comprising:a substrate having a trailing edge first surface adjacent the gas flow path; a bond coat applied to the trailing edge first surface; at least one coating material overlying the bond coat, an outer portion of the coating material forming the gas flow path surface; at least one channel in the substrate, the channel extending through the substrate between a first and second end, the first end of the substrate channel terminating in proximity to the trailing edge first surface of the substrate adjacent to the flow path surface, the second end of the substrate channel in fluid communication with a cooling fluid supply; at least one micro channel formed by the shadowing of the at least one coating material to a structured micro groove positioned between the first surface of the substrate and the outer surface of the coating material in a generally axial direction, the micro channel extending substantially parallel to the first surface of the substrate for a predetermined length, the micro channel in fluid communication with the first end of the substrate channel; and, means for expelling cooling fluid from the micro channel.