Cooling channels for gas turbine engine component
US10107128B2 · kind B2 · utility
25Cited by
15References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 20, 2015 |
| Grant date | Oct 23, 2018 |
| Priority date | — |
| Expiry date | Feb 15, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component includes a wall portion and a leading edge cooling channel that extends through the wall portion. The leading edge cooling channel includes at least one first cooling passage separated from at least one serpentine cooling passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.