Gas turbine engine composite blade
US8419374B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 14, 2009 |
| Grant date | Apr 16, 2013 |
| Priority date | — |
| Expiry date | Sep 7, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.