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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Bibliographic Details
Main Authors WALUNJ, Jalindar Appa, JAISWAL, Shashwat Swami, WASSYNGER, Stephen Paul, ZHANG, Xiuzhang James
Format Patent
LanguageEnglish
French
German
Published 24.04.2024
Subjects
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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Summary: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.
Bibliography:Application Number: EP20180175821