LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE

LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE

Core assemblies for manufacturing airfoils (60) and airfoils made therefrom, the core assemblies having a leading edge hybrid skin core (160) positioned relative to a plurality of core bodies and configured to define a leading edge cavity (134) at a leading edge (100) of the manufactured airfoil. Th...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: CLUM, Carey, MONGILLO, Dominic J., Jr
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
CASTING
ENGINE PLANTS IN GENERAL
FOUNDRY MOULDING
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PERFORMING OPERATIONS
POWDER METALLURGY
STEAM ENGINES
TRANSPORTING
WEAPONS
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Beschreibung
Zusammenfassung:Core assemblies for manufacturing airfoils (60) and airfoils made therefrom, the core assemblies having a leading edge hybrid skin core (160) positioned relative to a plurality of core bodies and configured to define a leading edge cavity (134) at a leading edge (100) of the manufactured airfoil. The leading edge hybrid skin core (160) extends from a root region toward a tip region (98) in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.