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An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent on

An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.

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What is claimed is: 1. An axial divergent section slot nozzle for an engine comprising: a plurality of spaced apart divergent flaps; means for moving said divergent flaps; a bridge member positioned intermediate adjacent ones of said divergent flaps; each said bridge member including a bridge brack

What is claimed is: 1. An axial divergent section slot nozzle for an engine comprising: a plurality of spaced apart divergent flaps; means for moving said divergent flaps; a bridge member positioned intermediate adjacent ones of said divergent flaps; each said bridge member including a bridge bracket and a sealing element joined to said bridge bracket; said sealing element having an upper surface; and said bridge bracket having a lower surface which has a center point and end tips and which lower surface has a first portion extending from said center portion to a first one of said end tips which diverges from said upper surface of said sealing element and a second portion extending from said center point to a second one of said end tips which diverges from said upper surface of said sealing element. 2. An axial divergent section slot nozzle according to claim 1, wherein said divergent flaps move relative to said lower surface so that in an overexpanded condition of said nozzle having a first nozzle throat area, a first slot is created between said upper surface of said sealing member and lower surfaces of said flaps. 3. An axial divergent section slot nozzle according to claim 2, wherein said divergent flaps move relative to said lower surfaces so that in an overexpanded condition of said nozzle having a second nozzle throat area smaller than said first nozzle throat area, a second slot smaller than said first slot is created between said upper surface of said seal member and said lower surfaces of said flaps. 4. An axial divergent section slot nozzle according to claim 1, further comprising means for joining said sealing element to said bridge bracket. 5. An axial divergent section slot nozzle according to claim 1, wherein said bridge bracket is shaped to allow variable slot size depending on nozzle throat jet area. 6. An axial divergent section slot nozzle according to claim 1, further comprising a plurality of said divergent flaps defining a nozzle surface area and said flaps being spaced apart by gaps which comprise from 3.0% to 30% of said nozzle throat surface area. 7. An axial divergent section slot nozzle according to claim 6, wherein said divergent flaps are spaced apart by gaps which comprise from 8.0% to 12.0% of said nozzle throat surface area. 8. An ejector nozzle bridge member comprising: a bridge bracket: a sealing element joined to said bridge bracket; said sealing element having an upper surface; and said bridge bracket having a lower surface which has a center point and end tips and which lower surface has a first portion extending from said center portion to a first one of said end tips which first portion diverges from said upper surface of said sealing element and a second portion extending from said center point to a second one of said end tips which second portion diverges from said upper surface of said sealing element, said first portion being joined to said second portion at said center point. 9. An ejector nozzle bridge member according to claim 8, further comprising said sealing element having a central portion and end portions at an angle to said central portion. 10. An ejector nozzle bridge member according to claim 8, further comprising: a backbone support attached to said sealing element; said bridge bracket fitting over said backbone support; and means for securing said bridge bracket on said backbone support. 11. An ejector nozzle bridge member according to claim 8, wherein said bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area. 12. A method for tailoring an exhaust plume of an engine, said method comprising the steps of: providing an engine with a nozzle having movable flaps which create a divergent zone; providing a bridge member between adjacent ones of said flaps; operating said engine and said flaps so as to create an overexpanded condition within said nozzle; positioning said flaps so as to tailor an exhaust plume from said nozzle to have a flow evenly distributed circumferentially; and said bridge member providing step comprising providing a bridge member having a sealing element and a bridge bracket having lower surfaces which diverge away from an upper surface of said sealing element. 13. A method according to claim 12, wherein said flap positioning step comprises moving adjacent ones of said flaps relative to said bridge member so as to create slots which allow ambient air to flow into said exhaust nozzle. 14. A method according to claim 12, wherein said flap positioning step comprises positioning said flaps so that gaps are created between adjacent ones of said flaps which occupy from 3.0% to 30% of a surface area of said nozzle. 15. A method according to claim 12, wherein said flap positioning step comprises positioning said flaps so that gaps are created between adjacent ones of said f laps which occupy from 8/0% to 12% of a surface area of said nozzle. 16. A method according to claim 12, wherein said bridge member providing step further comprises providing a bridge bracket having a diamond wedge shape. 17. A method for tailoring an exhaust plume of an engine, said method comprising the steps of: providing an engine with a nozzle having movable flaps which create a divergent zone; providing a bridge member between adjacent ones of said flaps; operating said engine and said flaps so as to create an overexpanded condition within said nozzle; positioning said flaps so as to tailor an exhaust plume from said nozzle to have a flow evenly distributed circumferentially; and said engine operating step comprising creating said overexpanded condition while said engine and said nozzle is operating in a STOVL condition. 18. A method for increasing the thrust produced by an axial divergent section slot nozzle comprising the steps of: providing a nozzle having a plurality of spaced apart divergent flaps; providing a plurality of bridge members having sealing elements which close a plurality of gaps between said divergent flaps, said bridge members providing step comprising providing a plurality of bridge members each having lower surfaces which diverge away from an upper surface of one of said sealing elements; and opening said gaps by operating said nozzle in an overexpanded condition and thereby creating a pressure gradient which allows ambient air surrounding said nozzle to flow into said nozzle. 19. A method according to claim 18, wherein said bridge member providing step further comprises providing a plurality of bridge members each having a sealing element which contacts a gas side of a pair of said flaps and a bridge bracket positioned on an air side of said flaps joined to said sealing element. 20. A method according to claim 19, wherein said bridge providing step further comprises providing a bridge bracket shaped to allow variable slot size depending on nozzle throat jet area. 21. A method according to claim 18, wherein said opening step comprises creating a pressure differential which causes each said sealing element to lose contact with said adjacent ones of said divergent flaps.