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A discharge nozzle is provided having a centerbody and a conduit enclosing the centerbody and is operable to receive exhaust flow from a turbine discharge of a gas turbine engine. In one form the centerbody is symmetric and extends along the flow direction, rising away from a reference axis to a max

A discharge nozzle is provided having a centerbody and a conduit enclosing the centerbody and is operable to receive exhaust flow from a turbine discharge of a gas turbine engine. In one form the centerbody is symmetric and extends along the flow direction, rising away from a reference axis to a maximum position before falling and converging on the reference axis. A set of rings is disposed between the centerbody and the conduit and are positioned between the centerbody and the conduit.

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1. An apparatus, comprising: a gas turbine engine including a turbine and a discharge nozzle downstream of the turbine, the discharge nozzle including: a conduit defining a passage in fluid communication with the turbine and an outlet downstream of the turbine, the outlet being structured to dischar

1. An apparatus, comprising: a gas turbine engine including a turbine and a discharge nozzle downstream of the turbine, the discharge nozzle including: a conduit defining a passage in fluid communication with the turbine and an outlet downstream of the turbine, the outlet being structured to discharge working fluid from the turbine;a centerbody positioned in the conduit along a first axis;several rings each circumscribing and offset from the centerbody and disposed between an outer flow wall of the conduit and the centerbody, the rings cooperating with the centerbody to reduce line of sight to the turbine through the nozzle, where line of sight is defined as a line disposed to a side of a centerline of the gas turbine engine and that extends from a location external of the discharge nozzle toward the turbine, and where said line does not cross the centerline of the gas turbine engine between the external location and the turbine; andone or more struts connected to the rings and one or more of the conduit and the centerbody, the struts being structured to position the rings in a nested relationship relative to one another between the turbine and the outlet;wherein a first portion of the passage extends a first distance perpendicular from the first axis, (b) a second portion of the passage upstream of the first portion extends a second distance perpendicular from the first axis, and (c) a third portion of the passage downstream of the first portion extends a third distance perpendicular from the first axis, the first distance being greater than the second distance and the third distance, and one or more of the several rings being within the first portion of the passage. 2. The apparatus of claim 1, wherein the nozzle defines a mixer downstream of the rings to intermix fluids of different temperatures. 3. The apparatus of claim 1, further comprising an aircraft carrying the gas turbine engine and the discharge nozzle to provide propulsive power to the aircraft. 4. The apparatus of claim 1, wherein the rings number at least three, each have an airfoil-shaped profile, and are structured with the centerbody to block a line of sight to the turbine. 5. The apparatus of claim 1, wherein the one or more struts each define a cooling passageway in fluid communication with a cooling fluid source. 6. The apparatus of claim 5, wherein the rings each include a cooling plenum to receive cooling fluid from the cooling passageway of at least one of the struts. 7. The apparatus of claim 1, further comprising means for cooling the rings and the centerbody. 8. The apparatus of claim 1, wherein the rings number between three and six and each include a plenum in fluid communication with one or more of a corresponding number of passageways each defined by a different one of the struts to receive a cooling fluid therethrough, the centerbody defines a cooling pathway connected to at least one of the passageways, and the nozzle includes a mixer for intermixing fluids of different temperatures. 9. The apparatus of claim 8, wherein the rings each have a reflexed airfoil shape and are staggered relative to one another along a centerline axis of the nozzle. 10. An apparatus, comprising: a gas turbine engine including a turbine and a nozzle downstream of the turbine, the nozzle including: a conduit defining a passage in fluid communication with the turbine and an outlet downstream of the turbine to receive hot working fluid therefrom;a centerbody positioned in the conduit along a first axis that extends from the turbine to the outlet such that a flow path is defined between the conduit and the centerbody; andseveral rings each circumscribing the centerbody, the rings cooperating with the centerbody to reduce line of sight of the turbine through the outlet to suppress infrared detection where line of sight is a line extending from an external observer to the turbine outlet and is offset to one side and does not cross a centerline of the gas turbine engine, the rings displaced from the centerbody and being positioned in a staggered relationship relative to one another along the first axis between the turbine and the outlet, the rings each having a different maximum dimension across the passage along a second axis perpendicular to the first axis;wherein a first portion of the passage extends a first distance perpendicular from the first axis, (b) a second portion of the passage upstream of the first portion extends a second distance perpendicular from the first axis, and (c) a third portion of the passage downstream of the first portion extends a third distance perpendicular from the first axis, the first distance being greater than the second distance and the third distance, and one or more of the several rings being within the first portion of the passage. 11. The apparatus of claim 10, wherein the nozzle defines means for mixing fluids of different temperatures downstream of the centerbody and the rings. 12. The apparatus of claim 10, further comprising an aircraft carrying the gas turbine engine and the nozzle to provide propulsive power to the aircraft. 13. The apparatus of claim 10, wherein the rings number at least three, each have an airfoil-shaped profile, and are structured with the centerbody to block the line of sight to the turbine. 14. The apparatus of claim 10, further comprising means for cooling the rings and the centerbody. 15. The apparatus of claim 10, wherein the rings each have a reflexed airfoil shape and are staggered relative to one another along a centerline axis of the nozzle. 16. An apparatus, comprising: a gas turbine engine including a turbine and a conduit, the conduit defining a passage in fluid communication with the turbine and an outlet downstream of the turbine wherein the passage includes a radially inner flow path surface and a radially outward flow path surface, a centerbody positioned along a central axis through the conduit which forms a flow passage between the conduit and the centerbody; several rings radially outward from the centerbody that circumscribe the centerbody, each one of the rings being in a nested relationship relative to at least one other of the rings, the rings being staggered along the central axis, and the rings being positioned in cooperation with the centerbody to reduce line of sight visibility of the turbine through the outlet; andwherein a first portion of the radially outer flow path surface of the passage extends a first distance perpendicular to the axis, a second portion of the radially outer flow path surface of the passage upstream of the first portion extends a second distance perpendicular to the central axis, and a third portion of the radially outer flow path surface of the passage downstream of the first portion extends a third distance perpendicular to the central axis, the first distance being greater than the second distance and the third distance, and one or more of the rings being within the first portion of the passage. 17. The apparatus of claim 16, further comprising a mixer downstream of the rings to intermix fluids of different temperatures. 18. The apparatus of claim 16, further comprising an aircraft carrying the gas turbine engine to provide propulsive power to the aircraft. 19. The apparatus of claim 16, wherein the rings number at least three, each have a reflexed airfoil shape. 20. The apparatus of claim 16, further comprising one or more struts each connected to the conduit and the centerbody and each defining a cooling passageway in fluid communication with a cooling fluid source. 21. The apparatus of claim 20, wherein the rings each include a cooling plenum to receive cooling fluid from the cooling passageway of at least one of the struts. 22. A method, comprising: operating a gas turbine engine including a turbine;discharging working fluid downstream through a conduit defining a passage in fluid communication with the turbine and an outlet downstream of the turbine;extending a centerbody along a first axis through the conduit and positioned radially inward from an inner surface of the conduit;circumscribing the centerbody with each of several rings, each one of the rings being in a nested relationship relative to at least one other of the rings, the rings displaced outward from the centerbody and being staggered along the first axis, and the rings being positioned in cooperation with the centerbody to reduce line of sight visibility of the turbine through the outlet; anddefining: (a) a first portion of the passage to extend a first distance perpendicular from the first axis, (b) a second portion of the passage upstream of the first portion to extend a second distance perpendicular from the first axis, and (c) a third portion of the passage downstream of the first portion to extend a third distance perpendicular from the first axis, the first distance being greater than the second distance and the third distance, and one or more of the rings being within the first portion of the passage. 23. The method of claim 22, which includes providing a mixer to intermix fluids of different temperatures downstream of the rings and the centerbody. 24. The method of claim 22, which includes cooling at least one of the rings by providing a cooling fluid through one or more struts in fluid communication therewith. 25. The method of claim 24, which includes radially extending the one or more struts between the centerbody and the conduit across the passage. 26. The method of claim 25, which includes providing the cooling fluid to the rings and the centerbody through the one or more struts. 27. The method of claim 22, wherein a first one of the rings has a different airfoil shape than a second one of the rings. 28. The method of claim 22, wherein an outer one of the rings is positioned closer to the turbine than an inner one of the rings.