For the first time the thermobarrier covering was applied in the mid-seventies during tests in section of the turbine of the test engine. It was already applied to the beginning of the 80th on nozzle shovels of gas-turbine engines of planes, and today is applied also on workers. In the near future load of thermobarrier coverings will only increase.

The baked enamels developed by NASA and the American bureau of the NBS standards were the very first ceramic coverings for space branch. Within the 1960th they it was used in aviation engines.

Subsequently the coverings put by means of a gas-flame dusting were developed. As a thermal barrier aluminum oxide, the zirconium oxide stabilized by oxide of magnesium and oxide of calcium was used. The last was the most suitable and was widely used. Nichrom or molybdenum was the material applied to communication of these coverings, but also it was used not always. However, the oxide of aluminum and oxide of zirconium stabilized by oxide of calcium had no necessary durability and were viable for advanced thermobarrier coverings.

The new era of TVS came from the middle of the 1970th of NASA developed a two-layer covering which was put with the APS method (air plasma spray, a plasma dusting in the air atmosphere). It consisted of a porous ceramic covering from oxide of the zirconium stabilized by oxide of yttrium (ZrO2-Y203) over the metal heat-resistant NiCrAIY of a binding covering put with the same method. (As M - Ni and/or Co) Union Carbide was one of the first TVS ZrO2-Y203/MSRAIY developers.

The first coverings of this sort on the basis of dioxide of zirconium contained from 12 to 20% of oxide of yttrium which was added for stabilization of a cubic phase. Subsequently, it was proved that the best performance data can be reached in case of lowering of the level of an oxide of yttrium to 6 and 8%.

Researches proved that Y203 surpasses by ZrO2/(6-8%) ZrO2/(12-20%) Y203 for advanced gas turbines, and these in turn surpass by TBC the systems on the basis of zirconium oxide offered earlier.

The offered coverings widely are used in modern gas-turbine engines for the purpose of fall of temperature of metal surfaces in sections of the turbine and the combustion chamber. They can be also applied in case of need to increase efficiency on fuel, to reduce emission of NOx and growth of power and draft.