Gas turbine engine airfoil
US11473434B2 · kind B2 · utility
2Cited by
2References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 16, 2019 |
| Grant date | Oct 18, 2022 |
| Priority date | — |
| Expiry date | Jul 15, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.