Patent ID: 7685825

Claim:
A nozzle assembly for a gas turbine engine comprising: a plurality of divergent flaps that are movable to adjust a cross-sectional area of an outlet of a nozzle; a plurality of convergent flaps and seals positioned upstream from said divergent flaps, said convergent flaps and seals being positioned to block flow of products of combustion from a location radially inwardly of said plurality of convergent flaps and seals to an internal housing radially outwardly of said convergent flaps and seals; and said convergent flaps and seals being connected to a liner facing inwardly and toward products of combustion, said liner being attached to said convergent flaps and seals by a bracket, said liner receiving a backing plate adjacent an upstream portion, said backing plate being positioned radially outward of an upstream liner portion, and said bracket being secured to a downstream liner portion, with said upstream and downstream liner portions being separate components providing a thermal break between the two.