FIELD: chemistry.
SUBSTANCE: invention relates to metallurgy and can be used to protect parts against high-temperature oxidation. The method for protection of gas turbine components from nickel alloy comprises vacuum deposition of the first coating layer of nickel-based alloy comprising, in weight.%: 0.5-3.0 Hf, 10.0-20.0 aluminum, 5.0-10.0 chromium, rest - nickel, on the outer surface of parts. Deposition of the second layer of aluminum alloy containing, in weight %: 0.5-3.0 Hf, 10,0-20,0 Ni, rest - Al is carried out. Then, vacuum annealing is carried out.
EFFECT: manufacturing of a heat-resistant coating at the operating temperatures of nickel-alloy gas turbine parts to 1250°C.
2 cl, 4 tbl, 3 ex
| Title | Year | Author | Number |
|---|---|---|---|
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|
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|
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| METHOD OF PROTECTION OF GAS TURBINE BLADES FROM HIGH-TEMPERATURE CORROSION | 1992 |
|
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| PROCEDURE FOR APPLICATION OF COMBINED HEAT RESISTANT COATING | 2009 |
|
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| METHOD OF APPLYING PROTECTIVE COATING ON GAS TURBINE BLADES | 1999 |
|
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| METHOD OF MACHINING METAL PART | 2007 |
|
RU2368701C2 |
