Axial flowing cooling passages for gas turbine engine components
US10100667B2 · kind B2 · utility
0Cited by
3References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 15, 2016 |
| Grant date | Oct 16, 2018 |
| Priority date | — |
| Expiry date | Nov 25, 2036 |
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 is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.