METHOD FOR PROTECTING TITANIUM ALLOY COMPRESSOR BLADES OF A GAS TURBINE ENGINE FROM DUST-ABRASIVE EROSION Russian patent published in 2022 - IPC C23C28/00 C23C14/16 C23C14/24 

FIELD: mechanical engineering.

SUBSTANCE: invention relates to mechanical engineering and can be used in aircraft engine construction and power turbine construction to protect the blade of a compressor blade of a gas turbine engine made of titanium alloys from dust abrasive erosion. The method includes hardening treatment, polishing and ion-implantation treatment of the blade feather, followed by applying an ion-plasma multilayer coating on the blade in the form of a specified number of pairs of layers in the form of a titanium-vanadium layer and a layer of titanium-vanadium-nitrogen compounds. Ion-implantation treatment of the blade feather is carried out with nitrogen ions with an energy of 20 to 26 keV and a dose of 1.5·10¹⁷ to 2.3·10¹⁷ cm^-2, an ion-plasma multilayer coating is applied with the ratio of titanium to vanadium in layers, wt.%: V from 14 to 28, the rest is Ti. A titanium-vanadium layer is applied with a thickness of 0.2 to 0.4 mcm. A layer of titanium compounds with vanadium and nitrogen is applied with a thickness of 0.9 to 2.1 mcm with a total thickness of the multilayer coating from 6.0 to 15.0 mcm.

EFFECT: resistance of the GTE compressor blades to erosive destruction is increased while ensuring the specified endurance and cyclic durability of the protected parts.

6 cl