Patent ID: 8800259

Claim:
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; and wherein 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.