The role of sublayer in improvement the thermal characteristics of plasma coatings

Purpose. Based on the analysis of thermally protected heat resistance of composite coating composed of two layers (first layer: underlayer ПН70Ю30 + basic protective coating ZrO2 + 10 % Ni and second layer: underlayer СоСrАlY + protectivecoating Аl2О3+Сr2О3 ) offer for better protection to the combustion chambers of gas turbine engines. Coating by gasthermal spraying.Method. Heat resistance of the coating was determined by conventional methods. Heat resistance was evaluated by weight increase per sample at his aging at 1000 °C for 5 hours. The cycle was repeated 3 times. Results. A comparative analysis of heat resistance alloys ЭП 648 and ЭИ 868, heat resistance and sublayers type ПН70Ю30 and СоСrАlY, and main type of protective coating was done ZrO2 + 10%Ni і Аl2О3+Сr2О3. It is shown that to protect the combustion chambers of gas turbine engines it is necessary to useplasma composition coating sublayer СоСrАlY and basic coating spinel Аl2О3+Сr2О3. Scientific innovation. Obtained new scientific data on the use of composite coatings termal protective combustion chambers and turbine engines by heat-shielding properties. The practical significance. Identified and studied, tested a new materials for composite coatings for termal protective combustion chambers of gas turbine engines and provided recomendations for propagation in the coating industry.