Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines
US7762057B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 5, 2007 |
| Grant date | Jul 27, 2010 |
| Priority date | — |
| Expiry date | May 3, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K3/077
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is positioned substantially coaxial with the engine shroud and extends forwardly into the fan duct to provide an interstitial mixer duct between the mixer duct shell and the core engine shroud. The aft portion of the mixer duct shell extends over a turbine exhaust frame, an attached mixer (if included), and a tail cone exhaust plug. The mixer duct shell can reduce noise and plume exhaust heat radiated from aircraft turbofan engines.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.