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In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high

In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.

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1. A thrust vectoring device useful for aircraft, the device comprising: a nozzle having an upstream portion structured to flow an exhaust stream from a turbomachinery component of a gas turbine engine, the nozzle also having a first injection discharge opening located at a first flow stream locatio

1. A thrust vectoring device useful for aircraft, the device comprising: a nozzle having an upstream portion structured to flow an exhaust stream from a turbomachinery component of a gas turbine engine, the nozzle also having a first injection discharge opening located at a first flow stream location in the nozzle and operable for flowing fluid in a tangential direction relative to a surface of the nozzle, and a second injection discharge opening located at a second flow stream location and operable for flowing fluid in a non-tangential direction relative to the surface of the nozzle, the first injection discharge opening and the second injection discharge opening structured to receive a discharge stream from a gas path from within the gas turbine engine and direct the discharge stream to alter a direction of the exhaust stream that is flowed through the nozzle;wherein the first flow stream location is coincident with or upstream of the second flow stream location;wherein the first injection discharge opening is located on one side of the nozzle and the second injection discharge opening is located on another side of the nozzle, wherein the first injection discharge opening and the second injection discharge opening are collectively referred to as an injection discharge subsystem; andwherein the nozzle includes a plurality of injection discharge subsystems, the plurality of injection discharge subsystems operable together to produce a change in direction of a nozzle flow stream;wherein the first injection discharge opening is a coanda injector and the second injection discharge opening is a fluidic injector, and wherein at least one of the injection discharge subsystems includes the first flow stream location to be axially coincident with the second flow stream location. 2. The thrust vectoring device of claim 1, wherein the first injection discharge opening is located on the opposite side of the nozzle as the second injection discharge opening. 3. The thrust vectoring device of claim 1, wherein the nozzle is coupled to the gas turbine engine, the gas turbine engine including a compressor in fluid communication with both the coanda injector and the fluidic injector. 4. The thrust vectoring device of claim 1, wherein the compressor is capable of providing up to about 3% of the gas turbine engine airflow to at least one of the first injection discharge opening and the second injection discharge opening. 5. The thrust vectoring device of claim 1, wherein the nozzle is a convergent-divergent nozzle. 6. The thrust vectoring device of claim 1, wherein the second injection discharge opening is oriented substantially normal to a nozzle surface. 7. The thrust vectoring device of claim 1, wherein a cross sectional shape of the nozzle comprises one of a circle, quadrilateral, a triangle, and an ellipse. 8. The thrust vectoring device of claim 1, wherein the nozzle is a high pressure ratio nozzle operable at pressure ratios greater than about 2.0. 9. The thrust vectoring device of claim 8, wherein the nozzle is operable to vector a nozzle fluid flow greater than about 2 degrees from a nozzle axis. 10. The thrust vectoring device of claim 9, wherein the nozzle is operable to vector a nozzle fluid flow to at least 10 degrees. 11. The thrust vectoring device of claim 1, wherein the nozzle is a supersonic nozzle. 12. An apparatus comprising: an aircraft nozzle operable to convey a flow streama first injector pair paired means for vectoring the flow stream of the nozzle; anda second injector pair for vectoring the flow stream of the nozzle located opposite the first injector pair;wherein the first injector pair includes a coanda injector at a first stream location and a fluidic injector at a second stream location;wherein the second injector pair includes a coanda injector at the first stream location and a fluidic injector at the second stream location;wherein the coanda injectors operable for flowing fluid in a tangential direction relative to a surface of the aircraft nozzle, and the fluidic injectors operable for flowing fluid in a non-tangential direction relative to the surface of the aircraft nozzle;wherein the first stream location is axially coincident with the second stream location. 13. The apparatus of claim 12, wherein the fluidic injector of the first injector pair produces a separated flow region on one side of the nozzle and wherein the coanda injector of the second injector pair adds momentum to the flow stream on an opposite side of the nozzle; and wherein the fluidic injector of the second injector pair produces a separated flow region on one side of the nozzle and wherein the coanda injector of the second injector pair adds momentum to the flow stream on an opposite side of the nozzle. 14. The apparatus of claim 12, where the aircraft nozzle is defined by a gas turbine engine nozzle. 15. The apparatus of claim 14, wherein the gas turbine engine nozzle is operable at pressure ratios greater than about 2.0, and the first injector pair and second injector pair are operable to vector the flow stream to angles greater than about 2 degrees. 16. A method comprising: operating a gas turbine engine to produce an exhaust flow;flowing the exhaust flow through a converging diverging nozzle;routing pressurized air to a plurality of fluidic injectors and a plurality of coanda injectors, wherein the coanda injectors operable for flowing fluid in a tangential direction relative to a surface of the nozzle, and the fluidic injectors operable for flowing fluid in a non-tangential direction relative to the surface of the nozzle;the plurality of fluidic injectors each located in separate regions of the converging diverging nozzle and paired with the plurality of coanda injectors to form at least a first injector pair and a second injector pair;wherein the first injector pair includes a coanda injector at a first stream location and a fluidic injector at a second stream location;wherein the second injector pair includes a coanda injector at the first stream location and a fluidic injector at the second stream location;wherein the first stream location is axially coincident with the second stream location;injecting pressurized air into the nozzle through the plurality of fluidic injectors and the plurality of coanda injectors, wherein the injecting includes providing a delivery of pressurized air through the plurality of fluidic injectors at a position coincident with delivery of pressurized air through the plurality of coanda injectors; andgenerating a thrust vector angle. 17. The method of claim 16, which further includes vectoring the exhaust flow with the plurality of fluidic injectors and the plurality of coanda injectors, wherein the injecting includes providing a delivery of pressurized air through the plurality of fluidic injectors at a position coincident with the delivery of pressurized air through the plurality of coanda injectors. 18. The method of claim 16, wherein the generating includes producing a thrust vector angle up to at least about 10 degrees. 19. The method of claim 16, which further includes controlling an aircraft by generating the thrust vector angle. 20. The method of claim 16, wherein the generating of a thrust vector angle further includes separating a flow in one area of the nozzle.