| 摘要 |
FIELD: mechanical engineering; manufacture of aircraft and power turbines; protection of parts working at high temperatures including large- sized parts of turbine hot passages. SUBSTANCE: proposed method includes preliminary treatment of surface of gas-turbine engine parts. Hat protective coat consists of three layers. First layer of nickel-based alloy is applied by gas thermal method. Second layer containing aluminum is applied by drossing method, after which layer is dried at temperature of 350 C for 30-60 min and vacuum diffusion annealing is performed. Surface of coat is treated by grinding powder. Third ceramic layer is applied by gas thermal method and is subjected to finishing by vibration polishing. Then, parts is subjected to vacuum heat treatment. EFFECT: increased service life of parts; low cost of process. 7 cl, 1 tbl, 1 ex
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