WEAR RESISTANT TURBINE BLADE TIP

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating (70). At least one turbine blade has sides and a tip and at least one seal member is located adjace...

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Bibliographische Detailangaben
1. Verfasser:	WUSATOWSKA-SARNEK, Agnieszka M
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 HEATING 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 WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating (70). At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer (67) and an abrasive coating (92) disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 254 micrometers and includes metal boride compounds.