Patent ID: 7617685

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; said convergent flaps and seals being connected to a liner facing inwardly and toward the products of combustion, said liner being attached to said convergent flaps and seals by a bracket, the attachment of the bracket to each of the flaps and seals provided by a threaded attachment member, said threaded attachment member having a head positioned on one radial side of said convergent flaps and seals, and a threaded portion extending radially to a second side of said convergent flaps and seals, and a nut being secured on said threaded attachment member on an opposed side of said bracket from said head, and there being structure for preventing rotation of said threaded attachment member as said nut is tightened onto said threaded attachment member; and wherein said threaded attachment member is positioned radially outwardly of said convergent flaps and seals, and said threaded portion extending radially inwardly of said threaded flaps and seals.