Cupped contour for gas turbine engine blade assembly
US10344597B2 · kind B2 · utility
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22References
19Claims
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Key dates
| Filing date | Aug 17, 2015 |
| Grant date | Jul 9, 2019 |
| Priority date | — |
| Expiry date | Jun 3, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.