TURBOMACHINE BLADE COOLING STRUCTURE

A blade (100) for a turbomachine includes an airfoil (114) extending radially between a root (118) and a tip with a tip shroud (116) coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also inc...

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Bibliographische Detailangaben
Hauptverfasser:	WALUNJ, Jalindar Appa, JAISWAL, Shashwat Swami, WASSYNGER, Stephen Paul, ZHANG, Xiuzhang James
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 blade (100) for a turbomachine includes an airfoil (114) extending radially between a root (118) and a tip with a tip shroud (116) coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail (150) extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity (158) is defined in a central portion of the platform. The tip shroud also includes a cooling channel (160) extending between the cooling cavity and an ejection slot (62) formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.