Variable geometry exhaust nozzle for a turbojet engine
US5359851A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 22, 1993 |
| Grant date | Nov 1, 1994 |
| Priority date | — |
| Expiry date | Nov 22, 2013 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/1223
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A variable geometry nozzle for a turbojet engine is disclosed wherein the adjustment of the cross-sectional area of the nozzle in a converging-diverging configuration is controlled by a single control system. The single control system varies the positions of both of the inner upstream and downstream flaps, as well as the outer flaps. A second control system operates simultaneously with the first control system to change the configuration of the nozzle to a converging-converging configuration. The inner, upstream flaps, which are pivotally connected to the downstream end of the turbojet exhaust duct, are controlled by an axially movable control ring which is connected to the controlled inner, upstream flaps via a link rod. The positions of the inner, downstream flaps, which have their upstream edges pivotally connected to a downstream edge of a corresponding upstream flap, are controlled by the movement of the upstream flap, as well as a connection with a cowling support via another link rod. The positions of the outer flaps are controlled by a cam which is operatively interposed between the control ring and the controlled, outer flaps.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.