TURBOMACHINE BLADE COOLING STRUCTURE

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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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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creator WALUNJ, Jalindar Appa
JAISWAL, Shashwat Swami
WASSYNGER, Stephen Paul
ZHANG, Xiuzhang James
description 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.
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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. 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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
title TURBOMACHINE BLADE COOLING STRUCTURE
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