GAS TURBINE BLADE REPAIR METHOD AND GAS TURBINE BLADE

A repair method for a gas turbine blade comprises: a step of removing a thermal barrier coating to expose at least part of a base material of the gas turbine blade; a first etching step of etching the exposed base material; a first identification step of identifying a base material deterioration lay...

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Bibliographische Detailangaben
Hauptverfasser:	ISHIDA, Masaharu, OKAYASU, Rin, DATE, Yasuki, YAMADA, Masahiro, NAMBA, Katsumi, KIMURA, Ryosuke, KAWACHI, Yosuke
Format:	Patent
Sprache:	eng
Schlagworte:	APPARATUS THEREFOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TO SURFACES, IN GENERAL BLASTING CHEMISTRY ELECTROLYTIC OR ELECTROPHORETIC PROCESSES ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METALLURGY NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS PROCESSES FOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TOSURFACES, IN GENERAL PROCESSES FOR THE ELECTROLYTIC REMOVAL OF MATERIALS FROMOBJECTS SPRAYING OR ATOMISING IN GENERAL STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A repair method for a gas turbine blade comprises: a step of removing a thermal barrier coating to expose at least part of a base material of the gas turbine blade; a first etching step of etching the exposed base material; a first identification step of identifying a base material deterioration layer that is harder than the base material from the etched base material; a first removal step of removing the identified base material deterioration layer if the base material deterioration layer is identified in the first identification step; and a step of applying a thermal barrier coating to the exposed base material after it is determined that there is no base material deterioration layer in the first identification step, or after the base material deterioration layer is removed in the first removal step.