Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines
US8726665B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 13, 2010 |
| Grant date | May 20, 2014 |
| Priority date | — |
| Expiry date | Aug 13, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airborne mobile platform that has at least one turbofan engine assembly having a fan driven by a core engine, a short nacelle around the fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is disposed substantially coaxial with and extending forwardly into the fan exhaust duct to provide a mixer duct between the mixer duct shell and a core engine shroud of the core engine. At least a portion of the mixer duct shell has a honeycomb core structure having an inner surface and an outer surface, with an acoustic lining on one of the inner or outer surfaces. The acoustic lining attenuates sound emanating from the turbofan engine assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.