Patent ID: 7784735
Filing Date: 2010-08-31
Classification: B64D,F02K,Y02T

Abstract:
1. An aircraft nacelle comprising: a cowling defining an internal volume and having leading and trailing ends relative to the direction of travel; an engine housed in the internal volume of the cowling; an annular flow channel for a secondary thrust flow, constructed between the engine and the cowling; a thrust reverser positioned at the trailing end of the cowling for movement between two positions, a first in which the thrust reverser forms the trailing end of the cowling where the trailing end includes internal and external flow surfaces and a second in which the thrust reverser blocks the annular flow channel and directs the secondary thrust flow out of the cowling towards the leading end for forming a reverse flow from only the secondary thrust flow; said thrust reverser further comprising; a plurality of static link rods constructed in the cowling, spaced about a circumference of the cowling and extending towards the trailing end; a plurality of doors, each mounted on adjacent static link rods, at the trailing ends of said static link rods, for pivoting movement thereon about an axis transverse to the static link rods where a trailing end of each of the plurality of doors forms the trailing end of the cowling including the internal and external flow surfaces at a tip of the trailing edge; and an actuator system operatively connected to respective doors to pivot the doors between the first and second positions.