SHAPE RECESSED SURFACE COOLING AIR FEED HOLE BLOCKAGE PREVENTER FOR A GAS TURBINE ENGINE

SHAPE RECESSED SURFACE COOLING AIR FEED HOLE BLOCKAGE PREVENTER FOR A GAS TURBINE ENGINE

A vane ring (68; 70) for a gas turbine engine component includes a multiple of vanes (72; 74) that extend between an inner vane platform (76; 78) and an outer vane platform (80; 82), each of the multiple of vanes (72; 74) contains an airfoil cooling circuit (102) that receives cooling airflow (C) th...

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Bibliographische Detailangaben
Hauptverfasser: COSHER, Christopher, McMAHON, Shawn M, BARGER, David, LUNDGREEN, Ryan, TRINDADE, Ricardo, MADONNA, Nicholas J, HASSAN, Mohamed, PRENTER, Robin, PERRON, Christopher, ANIELLO, Justin M, GAUTSCHI, Steven Bruce, BARTLING, Brett Alan
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 vane ring (68; 70) for a gas turbine engine component includes a multiple of vanes (72; 74) that extend between an inner vane platform (76; 78) and an outer vane platform (80; 82), each of the multiple of vanes (72; 74) contains an airfoil cooling circuit (102) that receives cooling airflow (C) through a feed passage located in the outer vane platform (80; 82) and an extension from the outer vane platform (80; 82), the extension comprises a metering passage in communication with the feed passage.