Turbine airfoil cooling system with leading edge impingement cooling system turbine blade investment casting using film hole protrusions for integral wall thickness control
AssigneesSiemens Aktiengesellschaft, Mikro Systems, Inc.
InventorsChing-Pang Lee, Nan Jiang
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Abstract
A method of forming an airfoil (12), including: abutting end faces (72) of cantilevered film hole protrusions (64) extending from a ceramic core (50) against an inner surface (80) of a wax die (68) to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes (34) in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes (102) formed by the film hole protrusions during the casting step.
Claims8
A method of forming an airfoil, comprising:
- forming film hole protrusions on a ceramic core at locations that correspond to locations of select film cooling holes within a pattern of film cooling holes on an airfoil formed by the ceramic core;
- using the film hole protrusions to hold the ceramic core in a fixed positional relationship with a wax die while forming a wax pattern around the ceramic core;
- removing the wax die;
- forming a ceramic shell that surrounds the wax pattern and contacts surfaces of the film hole protrusions;
- removing the wax pattern;
- using the film hole protrusions to hold the ceramic core in a fixed positional relationship with the ceramic shell while casting the airfoil around the ceramic core;
- and
- machining film cooling holes in the airfoil after the casting step to form the pattern of film cooling holes comprising the film cooling holes formed by the machining step and separate cast film cooling holes formed by the film hole protrusions during the casting step.
Dependencies are inferred from the claim text.