Top coating system for industrial turbine nozzle airfoils and other hot gas path components and related method

A turbine component (56) adapted for use in a hot gas path of a gas turbine having a thermal barrier coating (62) on at least one surface portion thereof, the turbine component further comprising a protective top coating (64) of predetermined thickness, the thickness determined as a function of in-u...

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Bibliographische Detailangaben
Hauptverfasser:	BRUCE, KEVIN LEON, MEYER, ROBERT CARL, DEBELLIS, LISA, STOWELL, WILLIAM R, SEAL, MICHAEL DAMIAN, CLARE, JAMES H, ARNESS, BRIAN P, SKOOG, ANDREW JAY, MURPHY, JANE ANN, MARKS, PAUL THOMAS, ROWE, RAYMOND GRANT, MCGOVERN, TARA E, ROLING, MATHEW CURTIS
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	ADHESIVES AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CHEMICAL PAINT OR INK REMOVERS 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 COMPOSITIONS, e.g. PAINTS, VARNISHES ORLACQUERS COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CORRECTING FLUIDS DIFFUSION TREATMENT OF METALLIC MATERIAL DYES ENGINE PLANTS IN GENERAL FILLING PASTES GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL INKS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METALLURGY MISCELLANEOUS APPLICATIONS OF MATERIALS MISCELLANEOUS COMPOSITIONS NATURAL RESINS NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PAINTS PASTES OR SOLIDS FOR COLOURING OR PRINTING POLISHES STEAM ENGINES SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION USE OF MATERIALS THEREFOR WEAPONS WOODSTAINS
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Beschreibung
Zusammenfassung:	A turbine component (56) adapted for use in a hot gas path of a gas turbine having a thermal barrier coating (62) on at least one surface portion thereof, the turbine component further comprising a protective top coating (64) of predetermined thickness, the thickness determined as a function of in-use temperature of the thermal barrier coating.