Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components 940053
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.
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, https://doi.org/10.4271/940053. Download Citation
Author(s):
Thomas W. Bleeks, Glen H. Graham
Pages: 4
Event:
International Pacific Air & Space Technolgy Conference
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
International Pacific Air and Space Technology Conference Proceedings-P-272
Related Topics:
Combustion chambers
Engine components
Jet engines
Gas turbines
Commercial aircraft
Coatings, colorants, and finishes
Combustion and combustion processes
Ceramics
Chemicals
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