The use of thermal barrier coatings on high-pressure turbine components can improve gas turbine efficiency through reduction of cooling airflow. However, the risk involved in reducing cooling airflow requires a highly reliable thermal barrier coating. This increased reliability will be achieved through several complementary approaches. Material and process development, life prediction method development and engine service experience. The two processes available for deposition of thermal barrier coatings (plasma spray and physical vapor deposition) are compared, and the advantages and disadvantages of each discussed as they apply to gas turbine components. The results of bond coat material development which has increased the thermal cycle life of plasma spray thermal barrier coatings are presented. Improvements were achieved by two methods: (1) the use of creep-resistant NiCoCrAlY bond coat compositions and (2) overaluminiding of the bond coat for improved oxidation resistance. Results of engine testing of thermal barrier coatings in an environment that produces hot corrosion are also presented.
Thermal barrier coatings for gas turbine use
Thermische Schutzschichten fuer den Einsatz in Gasturbinen
Materials Science and Engineering, Part A ; A120/121 , 1-2 ; 433-440
1989
8 Seiten, 14 Bilder, 2 Tabellen, 7 Quellen
Aufsatz (Zeitschrift)
Englisch
HOCHTEMPERATURSCHUTZSCHICHT , KORROSIONSSCHUTZSCHICHT , HOCHTEMPERATURWERKSTOFF , MORPHOLOGIE , KORROSIONSSCHUTZ , HOCHTEMPERATURKORROSION , GASTURBINE , PLASMASPRITZEN , PHYSIKALISCHES AUFDAMPFEN , ALUMINIEREN , TEMPERATURWECHSELFESTIGKEIT , KRIECHFESTIGKEIT , BESCHICHTUNGSVERFAHREN , HAFTFESTIGKEIT , OXIDSCHICHT , ZUNDER , BINDEMITTEL
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