Standard Article

Thermal Barrier Coatings

Materials Technology

High Temperature Materials

  1. Shiladitya Paul

Published Online: 15 DEC 2010

DOI: 10.1002/9780470686652.eae225

Encyclopedia of Aerospace Engineering

Encyclopedia of Aerospace Engineering

How to Cite

Paul, S. 2010. Thermal Barrier Coatings. Encyclopedia of Aerospace Engineering. .

Author Information

  1. TWI, Metallurgy, Corrosion and Surfacing Technology Group, Cambridge, UK

Publication History

  1. 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;
  • zirconia;
  • plasma spray;
  • EB-PVD;
  • failure mechanisms;
  • porosity;
  • ceramic coatings;
  • thermal conductivity