遮熱コーティングの補修方法並びに当該方法で形成された補修コーティング

Japanese Patent JP4416363

B2

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 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 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.

William Randolph Stowell
Robert Alan Johnson
Andrew Jay Scoog
Joseph Thomas Begovic, Junior
Thomas Walter Lenz
Jane Ann Murphy
Chin-Pan Lee
Daniel Peter Ifkovic, Jr.

JP2001313360A

February 17, 2010

October 11, 2001

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GENERAL ELECTRIC COMPANY

C23C4/10; C23C26/00; C23C18/06; F01D5/28; C23C18/12; C23C24/08; C23C28/00; F02C7/00

JP54181B2
JP10310482A
JP11246261A

US5723078

Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa

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