Abstract: A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.

Abstract: An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes at a downstream portion, and cooling air channels disposed within the divergent flap and seal, and communicating at a first end with the inlet holes and at a second end with the exit holes for conducting cooling air therethrough. Some of the exit holes of the divergent flap are disposed along lateral edge regions thereof. The divergent seals are interposed between adjacent divergent flaps, and each include lateral edge regions extending laterally beyond the exit holes. The lateral edge regions of each divergent seal have an outer surface overlying at least a portion of the exit holes of an adjacent divergent flap.

Abstract: A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling channels with respective intakes and outlets. As the nozzle transitions between positions, the divergent flap seals move relative a divergent flap longitudinal axis to modulate the cooling airflow which enters the separate intakes.

Abstract: A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A projection 56, which resides on the divergent flaps, extends radially inwardly from the nozzle. The nozzle also includes a coolant flowpath comprising an interior space 44 in the nozzle, an intake 58 for admitting coolant C into the interior space, and a coolant outlet 60 aft of the intake for discharging the coolant from the interior space. The intake resides forward of the throat. During operation, a coolant film flows along the radially inner surface of the nozzle. The projection encourages a portion of the coolant film to enter and flow through the the coolant flowpath to convectively cool the nozzle.

Abstract: A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A projection 56, which resides on the divergent flaps, extends radially inwardly from the nozzle. The nozzle also includes a coolant flowpath comprising an interior space 44 in the nozzle, an intake 58 for admitting coolant C into the interior space, and a coolant outlet 60 aft of the intake for discharging the coolant from the interior space. The intake resides forward of the throat. During operation, a coolant film flows along the radially inner surface of the nozzle. The projection encourages a portion of the coolant film to enter and flow through the the coolant flowpath to convectively cool the nozzle.