Gas turbine engine airfoil
US8167567B2 · kind B2 · utility
57Cited by
18References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 17, 2008 |
| Grant date | May 1, 2012 |
| Priority date | — |
| Expiry date | Sep 26, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49337
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.