Exhaust mixing in turbofan aeroengines
US4577462A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Oct 26, 1984 |
| Grant date | Mar 25, 1986 |
| Priority date | — |
| Expiry date | Oct 26, 2004 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The core engine of a mixed exhaust turbofan aeroengine is provided with a conical afterbody. The normal outlet guide vanes which remove residual swirl from the turbine exhaust gases are dispensed with and replaced by ducts within an afterbody having entries which receive the hot gases in the same manner and at the same angle as the passages between the guide vanes would have done. The hot ducts, whose aspect ratio is preferably transformed between their upstream and downstream ends, extend through the afterbody in substantially straight paths to avoid aerodynamic losses, and intersect its conical surface to form preferably slot-like nozzles from which the turbine exhaust gases issue as flattened jets. The exhaust jets partake of the original axial and tangential/swirl velocity components of the turbine gases, plus a radial component (consequential upon the orientation of the ducts) to achieve good penetration of the bypass stream. Satisfactory mixing between the bypass stream and the jets is achieved because of the radial and tangential velocity components and because the bypass stream flows in sheets between the jets. No net swirl in the mixed stream through the propulsion nozzle …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.