FIELD: process engineering.
SUBSTANCE: invention relates to machine building and can be used at repair of hot stage of aircraft, marine and power plat gas turbine part, for example, nozzle blades made from nickel or cobalt alloys as multibank structures. Prior to reconditioning repair, multibank structure of nozzle blades is separated to separate elements in number corresponding to that of blades in said structure. Blades are subjected to flaw detection and repair cross-section line is selected on the blades. Faulty part of blade leading and trailing edges is cut off and inserts are made Inserts and blades are assembled and welded along the repair lines. Blades are heat processed and machined. Thereafter repaired blades are fitted at turbine stator body with clearance of 2-5 mm between said blades.
EFFECT: recovery of material structure and geometrical parameters, longer life at complex strain.
4 cl, 1 ex, 1 tbl
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| METHOD OF RESTORING GAS TURBINE BLADES FROM NICKEL AND COBALT ALLOYS | 1994 |
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| METHOD OF RECLAIMING OPERATING PROPERTIES OF VANES MADE FROM TITANIUM ALLOYS | 2009 |
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