Combination turbojet engine nozzle and thrust reverser
US5470020A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 6, 1994 |
| Grant date | Nov 28, 1995 |
| Priority date | — |
| Expiry date | Oct 6, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/33
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combination converging-diverging exhaust nozzle and thrust reverser for an aircraft turbojet engine is disclosed having a generally annular array of cold flaps extending from a downstream end of a cowling support structure and a generally annular, inner array of hot flaps, located radially inwardly of the cold flap array and extending downstream from an end of the hot gas exhaust duct. The annular array of hot gas flaps comprises two sets of hot flap arrays, an array of first hot flaps being pivotally attached to the downstream edge of the hot gas exhaust duct with the array of second hot flaps having upstream edges that are in contact with downstream edges of the array of first hot flaps. The positions of the arrays of the first and second hot flaps may be adjusted relative to a central longitudinal axis to form a converging-diverging nozzle with a variable cross-sectional area. The array of second hot flaps is also movable between a forward thrust position, wherein the upstream edges of the second hot flaps are urged into contact with the downstream edges of the first hot flaps and a reverse thrust position wherein the upstream edges of the second hot flaps are displaced away f…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.