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Please use this identifier to cite or link to this item: http://hdl.handle.net/1959.3/41673
- Title
- Mechanical behavior of thermal barrier coatings for gas turbine blades
- Author(s)
- Berndt, Christopher C.; Phucharoen, Woraphat; Chang, George C.
- Abstract
- Plasma-sprayed thermal barrier coatings (TBCs) will enable turbine components to operate at higher temperatures and lower cooling gas flow rates; thereby improving their efficiency. Future developments are limited by precise knowledge of the material properties and failure mechanisms of the coating system. Details of this nature are needed for realistic modelling of the coating system which will, in turn, promote advancements in coating technology. This paper details complementary experiments and analytical modelling which has been undertaken in order to define and measure the important failure processes for plasma-sprayed coatings.
- Publication type
- Conference paper
- Source
- NASA Conference Publications: Proceedings of the Turbine Engine Hot Section Technology Conference, Cleveland, Ohio, United States, 1984, pp. 155-166
- Publication year
- 1984
- Keyword(s)
- Aircraft engines; Coating acoustic emission response; Fatigue of materials; Finite Element Method; Mathematical techniques; TAT; TBC material data; TBCs; Tensile Adhesion Tests; Thermal Barrier Coatings; Thermal cycling tests
- Publisher
- National Aeronautics and Space Administration, Scientific and Technical Information Office
- ISBN
- 0191-7811 (series ISSN)
- Peer reviewed
