Thermal Barrier Coatings
High Temperature Materials
Published Online: 15 DEC 2010
Copyright © 2010 John Wiley & Sons, Ltd. All rights reserved.
Encyclopedia of Aerospace Engineering
How to Cite
Paul, S. 2010. Thermal Barrier Coatings. Encyclopedia of Aerospace Engineering. .
- Published Online: 15 DEC 2010
Modern gas turbine engines, both aircraft and industrial, operate under conditions of high temperature and stresses, and the engine components are also subjected to corrosion, oxidation, and abrasion. The ever-increasing demand of higher operating temperature for better efficiency has led to researchers being on a constant lookout for new materials. The present operating temperature of gas turbine engines is limited by the onset of melting, creep, or excessive oxidation of the structural parts. Thermal barrier coatings (TBCs), which comprise oxidation-resistant metallic and insulating ceramic layers, when deposited onto the hot sections of turbine engines improve their durability and efficiency. It is thus recognized that better understanding of TBC materials and their failure mechanisms must be gained to fully exploit the significant performance improvements they can offer.
In this short review, a description is given of the materials' issues involved in the development of TBCs together with a brief overview of the current TBC systems, their anatomy, failure mechanisms, and possible future progress.
- thermal barrier coatings (TBCs);
- gas turbines;
- plasma spray;
- failure mechanisms;
- ceramic coatings;
- thermal conductivity