Turbojet-engine thrust reverser with scoop-doors of adjustable exhaust cross-section
US6158211A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 16, 1999 |
| Grant date | Dec 12, 2000 |
| Priority date | — |
| Expiry date | Jun 16, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/70
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bypass turbojet-engine thrust reverser comprises at least one hollow, pivoting door (3) with an inner conduit (10), defined between an outer structure (4) of the door (3) and an inner structure (5) of the door (3), which guides flow through the door (3) when the door (3) is in a reverse thrust position. At least a downstream part of the outer structure (4) of the door (3) is independent of and displaceable relative to the inner structure (5) of the door (3) and is driven in a centrifugal direction relative to the inner structure (5) by a mechanical drive system such that a downstream exhaust cross-section (S2) of the inner conduit (10), which is less than an intake cross-section (S1) of the inner conduit (10) when the door (3) is in a forward thrust position, is at least equal to the intake cross-section (S1) when the door (3) is in the reverse thrust position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.