Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle
US6349539B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 11, 2000 |
| Grant date | Feb 26, 2002 |
| Priority date | — |
| Expiry date | Jul 11, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/33
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by linear actuators (20) anchored in the stationary structure (2). The linear actuators (20) are connected by a swivel (22) to the vectoring ring (13) and are affixed to the stationary structure (2) to absorb the tangential loads applied by the exhaust gases on the diverging flaps and to allow positioning the vectoring ring (13). Preferably the linear actuator (20) is connected by a sheath (25) to the vectoring ring (13), the sheath (25) slidable on the actuator case (26) and being displaceable in a radial plane passing through the turbojet-engine's axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.