Gas turbine engine components with optimized leading edge geometry
US10138748B2 · kind B2 · utility
0Cited by
1References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 15, 2016 |
| Grant date | Nov 27, 2018 |
| Priority date | — |
| Expiry date | Dec 11, 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 having 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 elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.