Gas turbine engine airfoil with leading edge trench and impingement cooling
US10240464B2 · kind B2 · utility
3Cited by
9References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 5, 2014 |
| Grant date | Mar 26, 2019 |
| Priority date | — |
| Expiry date | Dec 31, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.