Patent Number: 6,165,600

Title: Gas turbine engine component having a thermal-insulating multilayer ceramic coating

Abstract: A method of forming a multilayer ceramic coating system on a substrate that requires thermal protection from a hostile thermal environment. The method generally entails forming at least one tape that contains ceramic particles dispersed in an organic constituent, such as a binder and/or plasticizer. If a single tape is used, the tape is formed of multiple layers of different compositions and applied as a unit to the substrate, thereby forming at least an innermost layer and an outermost layer on the substrate. If multiple tapes are used, a first tape is applied to the substrate to form the innermost layer, and a second tape is applied to form the outermost layer. The tape/tapes are then sintered to form innermost and outermost ceramic layers, respectively, on the substrate. The tape/tapes are formed and processed such that the innermost ceramic layer has submicron voids to provide a desired level of porosity, while the outermost ceramic layer is thinner, smoother and less porous than the innermost ceramic layer.

Inventors: Ivkovich, Jr.; Daniel P. (Fairfield, OH), Skoog; Andrew J. (West Chester, OH), Murphy; Jane A. (Middletown, OH), Rentz; Thomas W. (Cincinnati, OH)

Assignee: General Electric Company

International Classification: B32B 18/00 (20060101); C04B 35/111 (20060101); C23C 28/04 (20060101); C23C 28/00 (20060101); F01D 5/28 (20060101); B32B 003/26 (); B64C 003/20 ()

Expiration Date: 12/26/2017