FIELD: mechanical engineering; turbines.
SUBSTANCE: according to proposed method protection cover plates are fitted on leading edge. Then surface of suction face of blade adjacent to protection cover plates and section of leading edges lower than protection cover plates are strengthened by application of erosionproof coating by gas plasma sectional surfacing with subsequent melting of coating and heat treatment of blade with applied coating. Thickness of applied coating should by from 0.5 to 0.7 mm, and clearance between sections, from 0.2 to0.5 mm.
EFFECT: improved erosion resistance of surface of upper part of turbine blade airfoil portion without effecting main performance characteristics of blade.
1 dwg
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