Cupped contour for gas turbine engine blade assembly
US11591914B2 · kind B2 · utility
0Cited by
8References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 30, 2019 |
| Grant date | Feb 28, 2023 |
| Priority date | — |
| Expiry date | Nov 11, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.