Discharge system of a separated twin-flow turbojet for an aircraft, corresponding turbojet and associated design method
US9915227B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 25, 2013 |
| Grant date | Mar 13, 2018 |
| Priority date | — |
| Expiry date | Feb 18, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.