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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Bibliographische Detailangaben
1. Verfasser:	DUELM, Bradley T
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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Beschreibung
Zusammenfassung:	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.