Patent ID: 7555904
Filing Date: 2009-07-07
Classification: F02K,F05D

Abstract:
1. 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 rear flaps and seals by a bracket, said bracket being attached to said liner by a separate mechanical fastener, said separate mechanical fasteners extending from one side of said liner, through an opening in said liner, through an opening in said bracket, and there being clearance between an outer periphery of said separate mechanical fastener and an inner periphery of said opening in said bracket, said clearance being greater in a first direction generally along an axis of said nozzle than in a direction taken perpendicular to said first direction.