Turbojet engine thrust reverser and exhaust nozzle assembly
US6185926A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 3, 2000 |
| Grant date | Feb 13, 2001 |
| Priority date | — |
| Expiry date | Feb 3, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An exhaust assembly for a jet powerplant of a supersonic airplane comprising a rear structure fitted with a thrust reverser. The rear structure includes a primary multi-flap nozzle of variable cross-section situated downstream of a primary duct, a secondary multi-flap nozzle of variable cross-section situated downstream of a secondary duct enclosing the primary duct and a fairing enclosing the secondary duct and fitted with a throat downstream of an exhaust orifice of the secondary nozzle, the throat being followed by a diverging portion. The thrust reverser comprises two eyelids affixed in a pivotable manner to the fairing, one on each side to of an axial plane of symmetry. The eyelids are movable between an active, thrust-reversal position wherein the eyelids project transversely into a gas jet downstream of the fairing to deflect the gas jet in a forward direction for thrust-reversal and an inactive, forward-thrust position wherein the eyelids are situated in an extension of the fairing. The two eyelids are each mounted on the fairing by two lateral linkrods which are freely pivotable relative to the fairing about a transverse axis in the vicinity of the axial plane of symmetry.…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.