Turbine blade with optimised cooling

A turbine blade for a turbomachine such as a turboprop or a turbojet, the blade including a root, a vane carried by the root and extending in a spanwise direction, ending at a tip, the vane including a pressure-side wall and a suction-side wall spaced apart from each other, and at least one duct con...

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Bibliographic Details
Main Authors Vollebregt, Matthieu Jean-Luc, Eneau, Patrice, Digard Brou De Cuissart, Sebastien, Dujol, Charlotte Marie
Format Patent
LanguageEnglish
Published 23.06.2020
Subjects
BLASTING
CASTING
ENGINE PLANTS IN GENERAL
FOUNDRY MOULDING
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PERFORMING OPERATIONS
POWDER METALLURGY
STEAM ENGINES
TRANSPORTING
WEAPONS
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Summary:A turbine blade for a turbomachine such as a turboprop or a turbojet, the blade including a root, a vane carried by the root and extending in a spanwise direction, ending at a tip, the vane including a pressure-side wall and a suction-side wall spaced apart from each other, and at least one duct configured to collect cooling air at the root and to make same flow in the vane in order to cool same; holes and/or slots made in the walls of same in order to discharge the cooling air out of the vane; an upper inner cavity located at the tip of the vane in order to cool same; and wherein at least one of the ducts directly supplies the upper cavity with cooling air collected in the root.
Bibliography:Application Number: US201515312688