Process for repairing metallic pieces especially turbine blades of a gas turbine motor

A process for repairing a metallic shroud of a gas turbine blade includes a step of removing a portion of an anti-wear layer to a removal depth that is greater than a depth of wear of the anti-wear layer. Further, the process includes a step of leaving a trace of the anti-wear layer to subsist, wher...

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Bibliographische Detailangaben
Hauptverfasser:	BOULNOIS MICHEL, CAUX JEAN-MARC, VARIN JEAN-JACQUES, HERAULT PATRICK, SAMPAIO CLEMENT, CHAREYRE FRANCIS, BOUSSABOUN HASSAN, CARUANA CHARLES, DEFROCOURT GERARD, BOUDEREAU CHRISTIAN
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBINED OPERATIONS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	A process for repairing a metallic shroud of a gas turbine blade includes a step of removing a portion of an anti-wear layer to a removal depth that is greater than a depth of wear of the anti-wear layer. Further, the process includes a step of leaving a trace of the anti-wear layer to subsist, wherein the trace of the anti-wear layer extends at least in a re-entrant zone of the Z profile of the blade. The process also includes a step of depositing a new layer of anti-wear material on the trace of the anti-wear layer.