Patent ID: 6076347
Filing Date: 2000-06-20
Classification: F02K

Abstract:
A bypass turbojet-engine thrust reverser comprising hollow, scoop type pivoting doors which, in the closed position during forward-thrust operation of the thrust reverser, form part of an external engine cowling and which, when pivoted so that upstream edges of the doors enter the bypass flow duct of the engine, the doors constitute flow-deflecting baffles while opening passages in the external cowling during reverse thrust operation;at least part of the flow deflected by the doors being conducted by interior openings in the scoop type doors;said thrust reverser further comprising a fixed cowling structure including an upstream portion located upstream of the doors, said upstream portion comprising a forward frame having a downstream structure; a downstream portion located downstream of the doors; and fixed longitudinal beams extending alongside the doors connecting the upstream end downstream portions;a movable upstream visor element located, when the reverser is in the forward thrust mode, between the upstream edge of each door and the upstream portion of the fixed cowling structure, with said visor covering the downstream structure of the forward frame;each said visor pivotally mounted to fixed structure and including a drive control system arranged such that, during reverse thrust operation, the visor uncovers the downstream structure of the forward frame and presents an optimized aerodynamic surface to the reverse flow stream deflected by a respective door so as to allow optimal guidance of the thrust reverse flow forwardly of the cowling while maintaining a reduced total cross section of the thrust reversal opening.