HIGH-POWER PLASMA EVAPORATION OF HEAT-INSULATING COATING ON GAS TURBINE BLADES AND DEVICE TO THIS END Russian patent published in 2015 - IPC C23C4/10 C23C28/00 C23C4/12 C23C30/00 F01D5/28 

FIELD: process engineering.

SUBSTANCE: invention relates to application of protective coating of gas turbine blades. Heat-resistant sublayer based on intermetallide nickel-aluminium phases (β+Y¹) and zirconium dioxide-based ceramic thermal barrier layer are produced on the blade root section by plasma evaporation in air by focused plasma jet at the evaporated particles velocity of 2400 m/s and temperature of 5000-12000 K. This produces, in the binder heat-resistant sublayer, the lengthwise laminar substructure of intermetallide grains while, in thermal barrier ceramic layer, the spheroidal grains of zirconium dioxide with tubular structure. Binder heat-resistant 200 mcm-deep sublayer is formed from the "ПНХ20К20Ю13-1"-brand powder mix with particles dispersion of 80 mcm at arc current I = 180 A, arc voltage U = 260 V, plasma-forming aid pressure P_air = 6.2 atm and carrier argon pressure P_Ar = 5.0 atm. Binder heat-resistant 150 mcm deep sublayer is formed from the "ЦрОИ"-7 brand powder mix with particles dispersion of 90 mcm at arc current I = 190 A, arc voltage U = 220 V, plasma-forming aid pressure P_air = 2.0 atm and carrier argon pressure P_Ar = 0.1 atm.

EFFECT: higher heat resistance, longer life.

5 dwg, 1 tbl