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Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components
ISSN: 0148-7191, e-ISSN: 2688-3627
Published March 01, 1994 by SAE International in United States
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This paper describes a chemical immersion process capable of removing ceramic thermal barrier coatings, high temperature oxidation resistant coatings, and, nickel-aluminide bond coat materials from gas turbine engine components typically found in commercial and military jet engines. This process was originally developed to remove thermal barrier coatings from JT-8D combustion chambers for commercial aircraft. Since then, the process has been utilized to remove a variety of MCrAlY coatings from commercial and military aircraft engines.
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CitationBleeks, T. and Graham, G., "Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components," SAE Technical Paper 940053, 1994, https://doi.org/10.4271/940053.
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