Gas turbine engine turbine blade tip cooling
US10436039B2 · kind B2 · utility
0Cited by
27References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 10, 2014 |
| Grant date | Oct 8, 2019 |
| Priority date | — |
| Expiry date | May 25, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02P10/25
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.