REDUNDANT ENTRY COOLING AIR FEED HOLE BLOCKAGE PREVENTER FOR A GAS TURBINE ENGINE

REDUNDANT ENTRY COOLING AIR FEED HOLE BLOCKAGE PREVENTER FOR A GAS TURBINE ENGINE

A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a respective one of a multiple of feed passages; a multipl...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: COSHER, Christopher, BARGER, David, LUNDGREEN, Ryan, MCMAHON, Shawn M, 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
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
Beschreibung
Zusammenfassung:A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.