Gas turbine engine trailing edge ejection holes
US10563518B2 · kind B2 · utility
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22References
29Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 15, 2016 |
| Grant date | Feb 18, 2020 |
| Priority date | — |
| Expiry date | Apr 14, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.