APPLICATION OF COMBINED thermal barrier coating on the turbine blades of GTE

摘要

method u043du0430u043du0435u0441u0435u043du0438u00a0 combined u0442u0435u043fu043bu043eu0437u0430u0449u0438u0442u043du043eu0433u043e u043fu043eu043au0440u044bu0442u0438u00a0 on turbine blades, comprising u0445u0440u043eu043cu043eu0430u043bu0438u0442u0438u0440u043eu0432u0430u043du0438u0435 in the powder mixture, the subsequent u0442u0435u0440u043cu043eu0432u0430u043au0443u0443u043cu043du0443u044e u043eu0431u0440u0430u0431 u043eu0442u043au0443,cathode ray coating u0441u043bu043eu00a0 ceramics zro2 - 8Y2u043e3 to the input edge of the blades and annealing u0434u043bu00a0 final u0444u043eu0440u043cu0438u0440u043eu0432u0430u043du0438u00a0 structure u043fu043eu043au0440u044bu0442u0438u00a0 zro2 - 8Y2u043e3 - + '- phase to the u0432u0445u043eu0434u043du044b x u043au0440u043eu043cu043au0430u0445 blades with shift + '- phase to the concentration of u0430u043bu044eu043cu0438u043du0438u00a0 16 to 18% at the other sites u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 blades, thebefore u043eu0442u0436u0438u0433u043eu043c u043fu043eu043au0440u044bu0442u0438u00a0 layer ceramics zro2 - 8Y2u043e3 at the entrance edge of the blades u043fu0440u043eu0432u043eu0434u00a0u0442 electronic u043bu0443u0447u0435u0432u044bu043c way coating u0441u043bu043eu00a0 ceramics zro2 - 11Y2O3 - 40u0430l2u043e3 thickness 10 - 1 5 microns with a on the input u043au0440u043eu043cu043au0430u0445 blades structure of zro2 - 11Y2u043e3 - 40u0430l3u043e3 [] - (zro2 - 8Y2O3) + '- phases.