Thrust reverser with adjustable section nozzle for aircraft jet engine
US5853148A · kind A · utility
51Cited by
10References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 17, 1996 |
| Grant date | Dec 29, 1998 |
| Priority date | — |
| Expiry date | Dec 17, 2016 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/72
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a thrust reverser for a bypass jet engine that reverses the fan flow. The thrust reverser is installed in the fixed outer cowl and is comprised of pivoting doors that block the fan flow in order to create reverse thrust. A translating annular nozzle is located aft of the pivoting doors in the stowed position, preventing in flight inadvertent deployment. When the nozzle are translated aft, the doors are free to pivot and, at the same time, the section of the fan nozzle can be adjusted to produce more or less fan flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.