Patent ID: 6599568
Filing Date: 2003-07-29
Classification: B32B,C04B,C23C,F01D,F05D,Y02T,Y10T

Abstract:
A method for cooling of the flow path surface region of an engine component used in a gas turbine engine comprising the steps of:channeling apertures having a diameter of about 0.002â€³ to about 0.008â€³ in a substrate of the component to allow passage of cooling fluid from a cooling fluid source to a surface of the substrate; applying a bond coat having a thickness of about 0.0005â€³ to about 0.005â€³ to the surface of the substrate such that the bond coat partially fills the apertures near exit orifices at the substrate surface; applying a first inner TBC layer having a first density having a thickness of at least about 0.003â€³ over the bond coat, such that the TBC fills at least a portion of the remainder of the exit orifices; applying a second intermediate ceramic layer on top of the first porous inner TBC layer, wherein the intermediate layer has a second density that is more dense than the first density of the inner TBC layer; applying a third outer TBC layer over the intermediate layer, wherein the outer TBC layer has a third density that is more dense than the first density of the inner TBC layer; and passing cooling fluid from the cooling fluid source through the apertures in the substrate and into the porous inner TBC layer.