FIELD: metallurgy.
SUBSTANCE: invention relates to metallurgy, namely to nickel-based superalloys, and can be used in the aviation industry, in particular, for the manufacture of single-crystal blades of a gas turbine engine. Nickel-based superalloy contains, in wt %: 4.0-6.0 chromium, 0.4-0.8 molybdenum, 2.5-3.5 rhenium, 6.2-6.6 tungsten, 5.2-5.7 aluminum, 0.0-1.6 titanium, 6.0-9.9 tantalum, 0.3-0.7 hafnium, 0.0-0.3 silicon, the rest-nickel and possible impurities. Proposed is monocrystalline blade (20A, 20B) for a gas turbine engine, made using a superalloy and having a protective coating containing a metal sublayer applied to the superalloy and a ceramic heat barrier applied to the metal sublayer.
EFFECT: alloy is characterized by high values of heat resistance and resistance to thermal fatigue, increasing the resistance of the thermal barrier to delamination.
10 cl, 1 dwg, 3 tbl, 5 ex
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