Patent ID: 6375425
Filing Date: 2002-04-23
Classification: C23C,F01D,Y02T,Y10T

Abstract:
A cooling system for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine comprising:at least one channel having a first and second end, the first end terminating in an exit orifice located on a surface of a substrate, the second end in fluid communication with a cooling circuit contained within a turbine engine component, wherein the channel has a diameter of about 0.0005â€³ to about 0.02â€³; a bond coat having a thickness of about 0.0005â€³ to about 0.005â€³ applied to the substrate surface, wherein the bond coat partially fills the exit orifice of the at least one channel at the first channel end; and, a TBC layer having a preselected density applied to the bond coat such that the TBC fills the remainder of the exit orifice at the first channel end, and having a thickness of at least about 0.003â€³ applied over the bond coat, the preselected density being sufficient to permit diffusion and discharge of a cooling fluid.