Ventilation system for a convergent divergent exhaust nozzle
US7296397B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 22, 2004 |
| Grant date | Nov 20, 2007 |
| Priority date | — |
| Expiry date | May 9, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing. The means of cooling the divergent flaps comprise an annular plenum chamber delimited downstream by said conical shell and fed with cooling air through drillings made in a boundary wall between said plenum chamber and the downstream end of said annular passage, a plurality of distribution cells surrounding the plenum chamber and linked to the latter, said cells being delimited downstream by said conical shell and being arranged around the X axis in the planes of symmetry of the follower flaps and telescopic pipelines each linking a cell to the follower divergent flap situated in the same plane of symmetry as …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.