METHOD OF PROTECTION OF GAS TURBINE BLADES FROM HIGH-TEMPERATURE CORROSION Russian patent published in 1995 - IPC

Abstract RU 2033474 C1

FIELD: protection of thermally-stressed parts from high-temperature gas corrosion; protection of working blades or turbines made of heat-resistant nickel alloys. SUBSTANCE: method consists in subsequent deposition of first layer of condensed coating on outer surface of airfoil portion of blade; coating is made of nickel alloy and contains the following components, mass-% : chromium, 14-16; aluminium, 10-13.5; tantalum, 1.5-4.5 and yttrium, 0.1-0.8. Subsequent deposition of second layer on base of aluminium and vacuum annealing are then performed. EFFECT: high heat resistance and heat proofness of coating as compared with similar coatings and increased service life of blades in modern gas-turbine engines. 1 tbl

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RU 2 033 474 C1

Authors

Mubojadzhjan S.A.

Budinovskij S.A.

Dates

1995-04-20—Published

1992-07-20—Filed