Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components
Date Published: 1994-03-01
Paper Number:940053
DOI: 10.4271/940053
Citation:
Bleeks, T. and Graham, G., "Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components," SAE Technical Paper 940053, 1994, doi:10.4271/940053.
Author(s):
Thomas W. Bleeks - Enthone-OMI Inc.
Glen H. Graham - Tinker Air Force Base
Abstract:
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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