Gas turbine blade repair method and gas turbine blade

A gas turbine blade repair method including: a step in which a thermal barrier coating is removed to expose at least part of a base material of a gas turbine blade; a first etching step in which the exposed base material is etched; a first identification step in which a base material deterioration l...

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Bibliographische Detailangaben
Hauptverfasser:	OKAYASU, RIN, KAWACHI, YOSUKE, ISHIDA, MASAHARU, KIMURA, RYOSUKE, DATE, YASUKI, NAMBA, KATSUMI, YAMADA, MASAHIRO
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine blade repair method including: a step in which a thermal barrier coating is removed to expose at least part of a base material of a gas turbine blade; a first etching step in which the exposed base material is etched; a first identification step in which a base material deterioration layer that is harder than the base material is identified from the etched base material; a first removal step in which the identified base material deterioration layer is removed; and a step in which, after a determination has been made in the first identification step that there is no base material deterioration layer or after the base material deterioration layer is removed in the first removal step, a thermal barrier coating is applied to the exposed base material.