Gas turbine engine airfoil
US8807951B2 · kind B2 · utility
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20Claims
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Assignee
Inventors
Key dates
| Filing date | May 21, 2013 |
| Grant date | Aug 19, 2014 |
| Priority date | — |
| Expiry date | May 21, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49337
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.