Patent ID: 6511762
Filing Date: 2003-01-28
Classification: B32B,C04B,C23C,F01D,F05D,Y02T,Y10T

Abstract:
A cooling system for cooling of the flow path surface region of an engine component used in a gas turbine engine comprising:a superalloy substrate at least one channel having a first and second end, the first end terminating in an exit orifice located on a surface of the substrate, the second end connecting to a cooling circuit located within the substrate, wherein the at least one 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; a first layer of ceramic inner TBC having a first porosity and having a thickness of at least about 0.003â€³ applied over the bond coat such that the porous TBC fills at least a portion of the remainder of the exit orifice of the at least one channel; a second layer of ceramic intermediate TBC applied to the first layer of TBC, wherein the intermediate layer has a second porosity less than the first porosity so that it is more dense than the first, inner TBC layer; and a third layer of ceramic outer TBC applied to the second layer of TBC, wherein the third outer TBC layer has a third porosity so that it is less porous than the first inner TBC layer.