Pre-service oxidation of gas turbine disks and seals

A gas turbine component, such as a turbine disk or a rotating seal, is fabricated by furnishing a substrate (70) shaped as a gas turbine component made of a nickel-base superalloy, and oxidizing the surface (72) of the substrate (70) to produce an oxidized substrate (70) having thereon an oxide laye...

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Bibliographische Detailangaben
Hauptverfasser:	WEIMER, MICHAEL JAMES, HEANEY, JOSEPH ALOYSIUS, III, NAGARAJ, BANGALORE ASWATHA, SCHAEFFER, JON CONRAD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING 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 MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL DIFFUSION TREATMENT OF METALLIC MATERIAL ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METALLURGY NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine component, such as a turbine disk or a rotating seal, is fabricated by furnishing a substrate (70) shaped as a gas turbine component made of a nickel-base superalloy, and oxidizing the surface (72) of the substrate (70) to produce an oxidized substrate (70) having thereon an oxide layer (78) with a thickness of at least about 500 Angstroms. The step of oxidizing is performed prior to entry of the component into service and in an atmosphere that does not contain combustion gas. The oxidized gas turbine component is thereafter placed into service.