Abstract
This work analyses the characteristics of functional coatings obtained by vacuum ion-plasma sputtering. These coatings have three-layer multiphase structure created as a result of condensing aluminium and titanium according to a certain programme. The article presents the results of investigation into the heat-resistance of ion-plasma coatings based on Ti-Al-N for titanium alloy parts of gas turbine engines. Analysis of the oxidation process between a sample surface and coatings within the range of 500–825 °C was carried out. The basic features of the process of coating destruction under high-temperature oxidation conditions were determined by means of scanning electron microscopy. The results of the tests made it possible to state that the coatings developed are able to operate at temperatures of 600–750 °C.
Highlights
The increase in the operating efficiency of gas turbine engines (GTE) is related to the growth of their gas-dynamic cycle parameters and primarily to the growth of temperature before the turbine and the compressor compression ratio
The required reliability of compressor blades in this case can be reached by using rather expensive nickel-chromium and other heat-resistant alloys typical for gas turbines (Lahtin, Leontieva 1990). Another alternative is the use of titanium alloys usual for a compressor or alloyed steel with thermal barrier coatings (Dorfman et al 2004; Anikin et al 2009)
New technological solutions are required for the development of coatings that can assure the safe operation of aircraft
Summary
The increase in the operating efficiency of gas turbine engines (GTE) is related to the growth of their gas-dynamic cycle parameters and primarily to the growth of temperature before the turbine and the compressor compression ratio. At present the compression ratios of the compressors of powerful gas turbine engines reach 35–40 and are continuing to grow (Gunston 2007). The required reliability of compressor blades in this case can be reached by using rather expensive nickel-chromium and other heat-resistant alloys typical for gas turbines (Lahtin, Leontieva 1990). Another alternative is the use of titanium alloys usual for a compressor or alloyed steel with thermal barrier coatings (Dorfman et al 2004; Anikin et al 2009). New technological solutions are required for the development of coatings that can assure the safe operation of aircraft
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