Turbine blade root with microcircuit cooling passages
US9422817B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 31, 2012 |
| Grant date | Aug 23, 2016 |
| Priority date | — |
| Expiry date | Apr 13, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49316
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.