Patent ID: 7159383

Claim:
An apparatus for reducing noise generated by an aircraft gas turbine engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprises at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof, and the at least one gas injector has a plurality of gas exit ports having a shape which may be slotted ports, circular ports or a combination of slotted ports and circular ports.