Turbine airfoil cooling system with leading edge impingement cooling system turbine blade investment casting using film hole protrusions for integral wall thickness control
US10022790B2 · kind B2 · utility
12Cited by
11References
8Claims
0Family size
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Key dates
| Filing date | Jun 18, 2014 |
| Grant date | Jul 17, 2018 |
| Priority date | — |
| Expiry date | Jun 18, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/211
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.