Axial skin core cooling passage for a turbine engine component
US10323524B2 · kind B2 · utility
1Cited by
65References
29Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | May 8, 2015 |
| Grant date | Jun 18, 2019 |
| Priority date | — |
| Expiry date | Jan 27, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A component for use in a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A first skin core passage is defined immediately adjacent one of the first surface and the second surface. At least 80% of coolant entering the first skin core passage is expelled from the turbine engine component at the aft edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.