TURBULATORS FOR IMPROVED COOLING OF GAS TURBINE ENGINE COMPONENTS

A gas turbine engine component (32) includes a body defining a cooling airflow passage (42) thereat configured for directing a cooling airflow (44) therethrough. A plurality of turbulators (46) are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurali...

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Bibliographic Details
Main Author DUELM, Bradley T
Format Patent
LanguageEnglish
French
German
Published 21.06.2017
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 gas turbine engine component (32) includes a body defining a cooling airflow passage (42) thereat configured for directing a cooling airflow (44) therethrough. A plurality of turbulators (46) are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurality of turbulators (46) includes a plurality of facets extending outwardly from a central portion. The gas turbine engine component may be a blade outer airseal. The invention also extends to a gas turbine comprising a combustor and a plurality of said gas turbine engine components in fluid communication with the combustor.
Bibliography:Application Number: EP20160203379