FIELD: metallurgy.
SUBSTANCE: proposed method comprises sequential deposition in vacuum of first layer of condensed coat from nickel alloy on part outer surface and second aluminium-based layer to be annealed in vacuum. Said first layer contains the following elements, in wt %: chromium - 6-12.0, aluminium - 6-12.0, yttrium - 0.1-0.15, tantalum - 1.5-8.0, rhenium -0.3-2.5, hafnium - 0.2-1.5, nickel making the rest.
EFFECT: higher heat resistance at operating temperatures.
4 tbl, 3 ex
| Title | Year | Author | Number | 
|---|---|---|---|
| METHOD FOR PROTECTION OF GAS TURBINE COMPONENTS MADE FROM NICKEL ALLOYS | 2015 | 
 | RU2610188C1 | 
| METHOD OF PROTECTING BLADES AND NOZZLE ASSEMBLY OF GAS TURBINES | 2023 | 
 | RU2818096C1 | 
| METHOD OF PROTECTION OF THE BLADES OF THE GASEOUS TURBINES | 2004 | 
 | RU2280096C1 | 
| METHOD OF PROTECTION OF TURBINE ROTOR BLADES | 2004 | 
 | RU2283365C2 | 
| METHOD OF PROTECTION OF GAS TURBINE BLADES | 2000 | 
 | RU2190691C2 | 
| METHOD OF PROTECTING PARTS OF GAS TURBINES | 2023 | 
 | RU2818539C1 | 
| METHOD OF MACHINING METAL PART | 2007 | 
 | RU2368701C2 | 
| CASTING HEAT RESISTANT NICKEL-BASED ALLOY | 2015 | 
 | RU2626118C2 | 
| COMPOSITION FOR PRODUCTION OF CARBIDE BARRIER COATING ON PART OUT OF CARBON-FREE HEAT-RESISTANT NICKEL ALLOY | 2014 | 
 | RU2569610C2 | 
| METHOD OF APPLYING PROTECTIVE COATING ON GAS TURBINE BLADES | 1999 | 
 | RU2171315C2 | 
Authors
Dates
2012-06-10—Published
2011-06-22—Filed