METHOD FOR REPAIRING MOVING BLADE OF GAS TURBINE

PURPOSE:To form a dense layer and to increase the adhesive strength in the boundary layer of a repaired part by removing the area of a blade reduced in thickness by corrosion, building up MCrAlY thereon by reduced pressure plasma thermal spraying and subjecting this part to a diffusion heat treatmen...

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Bibliographische Detailangaben
1. Verfasser:	HIROTA NORIHIDE
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS ANDNON-FERROUS ALLOYS CHEMICAL SURFACE TREATMENT CHEMISTRY COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY IONIMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMBINED OPERATIONS DIFFUSION TREATMENT OF METALLIC MATERIAL ENGINE PLANTS IN GENERAL FERROUS OR NON-FERROUS ALLOYS HEATING INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR METALLURGY NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS STEAM ENGINES SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION TRANSPORTING TREATMENT OF ALLOYS OR NON-FERROUS METALS UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	PURPOSE:To form a dense layer and to increase the adhesive strength in the boundary layer of a repaired part by removing the area of a blade reduced in thickness by corrosion, building up MCrAlY thereon by reduced pressure plasma thermal spraying and subjecting this part to a diffusion heat treatment. CONSTITUTION:The area 2 reduced in thickness by corrosion of the moving blade 1 of the gas turbine consisting of a hardly weldable cemented carbide is completely removed by grit blasting, etc., and this part is shaped by machining. The MCrAlY (M: Ni, Co, CoNi, Fe, etc.) is then build-up thermally sprayed 4 by a reduced pressure plasma thermal spraying on this part at the thickness larger by about >=0.1mm than the thickness of the blade surface. The moving blade 1 of the gas turbine formed with such build-up thermal spraying 4 is charged into a vacuum atmosphere and is heated and held; thereafter, the vane is rapidly cooled to generate the counter diffusion between the base metal and the thermal spraying material, by which a diffused layer is formed. Finally, the profile surface is subjected to finishing to complete the repair.