Patent ID: 7377099

Claim:
A system for cooling lateral edge regions of an exhaust nozzle divergent seal for a gas turbine engine, the system comprising an axisymmetric nozzle including: a plurality of divergent flaps disposed about a central longitudinal axis of the nozzle, the divergent flaps each having an inner surface defining a plurality of cooling air inlet holes at an upstream portion, a plurality of cooling air exit holes at a downstream portion, and a plurality of cooling air channels disposed within the divergent flap and communicating at a first end with the inlet holes of the divergent flap and at a second end with the exit holes of the divergent flap for conducting cooling air therethrough, at least a portion of the exit holes of the divergent flap being disposed along lateral edge regions of the divergent flap; and a plurality of divergent seals disposed about the central longitudinal axis, the plurality of divergent seals being interposed between adjacent divergent flaps, the divergent seals each having an inner surface defining a plurality of cooling air inlet holes at an upstream portion, a plurality of cooling air exit holes at a downstream portion, and a plurality of cooling air channels disposed within the divergent seal and communicating at a first end with the inlet holes of the divergent seal and at a second end with the exit holes of the divergent seal for conducting cooling air therethrough, the plurality of divergent seals each including lateral edge regions extending laterally beyond the exit holes of the divergent seal, the lateral edge regions of each divergent seal having an outer surface being in overlying relationship with at least a portion of the exit holes defined in an associated adjacent divergent flap for cooling air to flow through said portion of the exit holes and thereby cool the lateral edge regions of the associated divergent seal.