Functionally gradient materials for thermal barrier coatings in advanced gas turbine systems
- Lehigh Univ., Bethlehem, PA (United States); and others
New designs for advanced gas turbine engines for power production are required to have higher operating temperatures in order to increase efficiency. However, elevated temperatures will increase the magnitude and severity of environmental degradation of critical turbine components (e.g. combustor parts, turbine blades, etc.). To offset this problem, the usage of thermal barrier coatings (TBCs) has become popular by allowing an increase in maximum inlet temperatures for an operating engine. Although thermal barrier technology is over thirty years old, the principle failure mechanism is the spallation of the ceramic coating at or near the ceramic/bond coat interface. Therefore, it is desirable to develop a coating that combines the thermal barrier qualities of the ceramic layer and the corrosion protection by the metallic bond coat without the detrimental effects associated with the localization of the ceramic/metal interface to a single plane.
- Research Organization:
- Clemson Univ., SC (United States). Energy Research Center
- Sponsoring Organization:
- USDOE, Washington, DC (United States)
- DOE Contract Number:
- FC21-92MC29061
- OSTI ID:
- 219513
- Report Number(s):
- DOE/MC/29061--96/C0659; CONF-9510109--30; ON: DE96008959
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
33 ADVANCED PROPULSION SYSTEMS
36 MATERIALS SCIENCE
COMPOSITE MATERIALS
CORROSION PROTECTION
ELECTRODEPOSITED COATINGS
FRACTURE PROPERTIES
GAS TURBINE ENGINES
INTERFACES
LANTHANUM PHOSPHATES
MATRIX MATERIALS
MICROSTRUCTURE
NICKEL ALLOYS
PROTECTIVE COATINGS
SAPPHIRE
TURBINE BLADES