METHOD FOR SELECTIVE SURFACE PROTECTION OF A GAS TURBINE BLADE WHICH HAS PREVIOUSLY BEEN IN SERVICE

A gas turbine blade (20) which has previously been in service is protected by cleaning the gas turbine blade (20), and then first depositing a platinum first layer on the airfoil (22) and the platform (28) of the gas turbine blade (20). Thereafter, a platinum second layer is deposited over the platf...

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Bibliographische Detailangaben
Hauptverfasser:	YOW, KWOK HENG, LANGLEY, NIGEL BRIAN THOMAS, CHEN, KENG NAM, HU, GENFA
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS APPARATUS THEREFOR BLASTING CHEMICAL SURFACE TREATMENT CHEMISTRY CLEANING OR DEGREASING OF METALLIC MATERIAL BY CHEMICALMETHODS OTHER THAN ELECTROLYSIS 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 COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DIFFUSION TREATMENT OF METALLIC MATERIAL ELECTROFORMING ELECTROLYTIC OR ELECTROPHORETIC PROCESSES ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METALLURGY MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25 NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTIONOF COATINGS STEAM ENGINES SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine blade (20) which has previously been in service is protected by cleaning the gas turbine blade (20), and then first depositing a platinum first layer on the airfoil (22) and the platform (28) of the gas turbine blade (20). Thereafter, a platinum second layer is deposited over the platform (28) but not the airfoil (22). A platinum- aluminide protective coating is formed by depositing an aluminum-containing layer (80) overlying both the platform (28) and the airfoil (22) and interdiffusing the platinum and the aluminum. Une aube (20) de turbine à gaz qui a précédemment été en service est protégée par nettoyage, puis une première couche de platine est déposée sur le profil d'aile (22) et la plate-forme (28) de l'aube (20) de turbine à gaz. Ensuite, une deuxième couche de platine est déposée sur la plate- forme (28) mais non sur le profil d'aile (22). Un revêtement protecteur d'aluminiure de platine est formé par déposition d'une couche contenant de l'aluminium (80) sur la plate-forme (28) et le profil d'aile (22) et par interdiffusion du platine et de l'aluminium.