Method of forming an airfoil having internal cooling passages

A method of forming an airfoil (104) having an internal cooling circuit (142), the internal cooling circuit including a flow path (130,132,134,136,138,140). An array of cylindrical pins (608) is formed on a selected portion of an outer surface of a core (600). Each pin (608) includes a top wall (614...

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Bibliographic Details
Main Authors SMOKE, JASON C, TAPIA, LUIS A, AGARWAL, VIVEK, MORRIS, MARK C, BAKER, WILLIAM C
Format Patent
LanguageEnglish
French
German
Published 20.08.2008
Subjects
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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Summary:A method of forming an airfoil (104) having an internal cooling circuit (142), the internal cooling circuit including a flow path (130,132,134,136,138,140). An array of cylindrical pins (608) is formed on a selected portion of an outer surface of a core (600). Each pin (608) includes a top wall (614), a cylindrical side wall (616), and a chamfered edge (618) therebetween. The core (600) is shaped similarly to the internal cooling circuit (142), and the selected portion of the core (600) is shaped similarly to the flow path (130-140). The airfoil (104) is formed around the core (600) and the core (600) is removed from the airfoil (104) to expose a roughened surface comprising a plurality of cylindrical depressions (144,146) on a surface of the airfoil (104) from which the selected core portion is removed. Each depression (144,146) includes a cylindrical sidewall (148) coupled to a bottom wall (150) by a chamfered edge (152) formed therebetween.
Bibliography:Application Number: EP20060116953