AIRFOIL HAVING DEAD-END TIP FLAG CAVITY AND CORRESPONDING CORE ASSEMBLY

AIRFOIL HAVING DEAD-END TIP FLAG CAVITY AND CORRESPONDING CORE ASSEMBLY

Airfoils for gas turbine engines are described. The airfoils (320) include an airfoil body extending between a platform (348) and a tip (322), the airfoil body having a leading edge (322), a trailing edge (324), a pressure side (326), and a suction side (328), a serpentine cavity formed within the a...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: NIEZELSKI, David A, TELLER, Bret M, SLAVENS, Thomas N, JENNINGS, Timothy J, MCBRIEN, John
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:Airfoils for gas turbine engines are described. The airfoils (320) include an airfoil body extending between a platform (348) and a tip (322), the airfoil body having a leading edge (322), a trailing edge (324), a pressure side (326), and a suction side (328), a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity (340), a down-pass serpentine cavity (342), and a trailing edge cavity (344), and a dead-end tip flag cavity (338) extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arranged between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall (366) located at a position between the leading edge and the trailing edge of the airfoil body. A corresponding core assembly for the formation of the airfoil is also provided.