BLADE FOR A GAS TURBINE AND CASTING TECHNIQUE METHOD FOR PRODUCING SAME

A blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trai...

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Bibliographic Details
Main Authors KRUECKELS JOERG, DUECKERSHOFF ROLAND, MCFEAT JOSE ANGUISOLA, WARDLE BRIAN KENNETH
Format Patent
LanguageEnglish
Published 29.09.2011
Subjects
BLASTING
CASTING
CASTING OF METALS
CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
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 blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity, to improve the transfer of heat between the wall of the blade and the cooling air. An improvement of the internal cooling is achieved by the turbulators or pins extending into the cavity in a direction which can be freely selected within an angular range.
Bibliography:Application Number: US20100961659