METHOD OF COMBINATION HEAT-RESISTANT COATING ON TURBINE BLADES OF GAS-TURBINE ENGINE

摘要

FIELD: metallurgy. ^ SUBSTANCE: method includes chrome-calorising in powder composition, following thermo-vacuum treatment by means of tempering, ceramic layer spatter ZrO2-8Y2O3 on front end edges of blades by electron-beam method and diffusion annealing for final formation of coating structure. Before the homogenising annealing on ceramic layer ZrO2-8Y2O3 by means of electron-beam method is spread ceramic layer ZrO2-11Y2O3-40Al2O3 of thickness 10-15 micrometer. Homogenising annealing is implemented with forming of coating structure on front end edges of blades, containing of [ZrO2-11Y2O3-40Al2O3]-(ZrO2-8Y2O3) - beta+gamma' - phase and turning into beta+gamma' - phase at the rest of blades areas. ^ EFFECT: increasing of durability and reliability enhancement of turbine blades. ^ 2 dwg, 1 ex