Component with repaired thermal barrier coating

Stock material or miscellaneous articles – Structurally defined web or sheet – Including variation in thickness

Reexamination Certificate

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C428S063000, C428S156000, C428S323000, C428S325000

Reexamination Certificate

active

06919121

ABSTRACT:
A method of repairing a thermal barrier coating (16) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating (16) on a component (10) that has suffered localized spallation (20) of the thermal barrier coating (16). After cleaning the surface area (22) of the component (10) exposed by the localized spallation (20), a ceramic paste (24) comprising a ceramic powder in a binder is applied to the surface area (22) of the component (10). The binder is then reacted to yield a ceramic-containing repair coating (26) that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating (26) has a ceramic matrix. The repair method can be performed while the component (10) remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.

REFERENCES:
patent: 4030936 (1977-06-01), Willis
patent: 4332618 (1982-06-01), Ballard
patent: 5626923 (1997-05-01), Fitzgibbons et al.
patent: 5723078 (1998-03-01), Nagaraj et al.
Lewis, Richard J., Hawley's Condensed Chemical Dictionary, John Wiley & Sons, nc., 13thed., pp. 872 and 960.

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