**2. Ceramic thermal barrier coatings and heating methods**

For the purpose of providing the serviceability of high-efficiency aircraft gas turbine engines and gas turbine plants of new generations, it is necessary to improve existing cooling systems, to design new refractory and ceramic high-temperature materials, and to enhance the protection of parts of the high-temperature section of gas turbine engines with the use of heat-resistant and refractory coatings [1-12]. Improvement of the internal heat removal system leads to the transformation of parts into heat exchangers, which is accompanied by an increase in the thermal stress and a decrease in the thermal cycle life. Currently widely used refractory materials based on nickel usually operate in gas turbine engines at maximum allowable temperatures. The gas temperature can be allowed to increase only in

Investigations of Thermal Barrier Coatings for Turbine Parts 131

depending on thickness *h* of ceramic coatings ZrO2 at gas thermal flow *q* = 1,8106 W/m2 and

different heat conductivity of coatings: *1* - 1,5 W/(mК);*2* - 0,8 W/(mК)

depending on thermal flows *q* at thickness *h =* 0,14 mm of ceramic coatings ZrO2 and

*t* on a surface of cooled GTE blades

*t* on a surface of cooled GTE blades

Fig. 1. Values of decrease of metal temperature

Fig. 2. Values of decrease of metal temperature

different heat conductivity: *1* - 1,5 W/(mК); *2* - 0,8 W/(mК)

the case where care is taken to restrict the passage of heat flow through the wall of the part. The heat flow from the gas to the wall of the base material of the part can be considerably reduced by means of either using a well-organized protective cooling without ejection or depositing thermal barrier coatings on the surface of the most strongly heated regions of the part.
