Thrust reverser integrating a variable exhaust area nozzle

Abstract From the Canadian patent

A thrust reverser for jet engines comprising a pair of symmetrical thrust reverses door members (30) which are pivotally mounted on an engine about an axis (40) which is substantially diametrical with respect to the exhaust nozzle of the engine the, doors having scarfed trailing edges (42) in order that they may pivot between stowed and deployed positions, a pair of pivotally mounted half shells (44) surrounding at least the trailing edges and defining a planar exhaust outlet for the engine; the pivot axes (40) for the doors is movable in order to vary the area of the exhaust outlet defined by the half-shells (44) depending upon the particular stage of flight.