Variable geometry turbojet engine exhaust nozzle
US5494221A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 19, 1995 |
| Grant date | Feb 27, 1996 |
| Priority date | — |
| Expiry date | Jan 19, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A variable geometry exhaust nozzle for a turbojet engine is disclosed having an array of outer flaps and an array of inner flaps radially spaced apart and extending about a central axis of the exhaust duct structure. The array of outer flaps comprises a plurality of outer flaps each having an upstream end pivotally attached to the engine duct structure. The array of inner flaps comprises a plurality of upstream inner flaps, each having an upstream edge pivotally attached to the engine duct structure and a plurality of downstream inner flaps each having an upstream edge portion pivotally attached to a downstream edge portion of a corresponding upstream inner flap. A control annulus is movably attached to the engine structure so as to be movable axially along the central axis and is connected to an actuator which moves the control annulus between upstream and downstream limit positions along the central axis. The control annulus is connected to the upstream and downstream inner flaps such that the axial components of the forces exerted by the control annulus on the connections to the upstream and downstream inner flaps extend in opposite directions. The control annulus is also connec…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.