Patent ID: 6617003
Filing Date: 2003-09-09
Classification: C23C,F01D,Y02T,Y10T

Abstract:
A cooling system for actively cooling a flow path surface region of a gas turbine hot section component extending into the gas flow path of a gas turbine, comprising:a substrate having a first surface adjacent the gas flow path; at least one coating material overlying the first surface of the substrate, the outer portion of the coating material forming the gas flow path surface; at least one channel in the substrate, the substrate channel extending through the substrate between a first and second end, the first end of the substrate channel terminating in proximity to the 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; and at least one micro channel having a cross section of predetermined size and configuration in fluid communication with the first end of the substrate channel, the micro channel positioned between the first surface of the substrate and the outer surface of the coating material, the micro channel extending substantially parallel to the first surface of the substrate for a predetermined length; and means for expelling cooling fluid from the micro channel.