This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Chemical Removal of Ceramic Thermal Barrier and Metallic Bond Coats from Gas Turbine Combustion Components
Annotation ability available
Sector:
Language:
English
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.
Recommended Content
Technical Paper | Smoke Reduction in Jet Engines Through Burner Design |
Technical Paper | Thermal Barrier Coatings for Monolithic Ceramic Low Heat Rejection Diesel Engine Components |
Aerospace Standard | SPARK PLUGS, AIRCRAFT ENGINE |
Authors
Topic
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.Also In
References
- Maricocchi, Anthony Martin, Brian “PVD TBC Experience on GE Aircraft Engines” Third Annual International Seminar Course, Functional Coatings In Industry Toronto, Canada October 1992
- Pratt & Whitney's Commercial Overhaul Standard Practices Manual, Service Process Operation Procedure SPOP # 319, Service Process Solution SPS #98
- Rolls Royce's General Overhaul Process Manuals, TSD594J-OP107 and TSD594-OP107
- Westphal V. Interturbine Germany GmbH January 1992
- Graham Glen Department of the Air Force, Oklahoma City Air Logistics center July 1993