Abstract: An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a centerline of the engine. The trailing edge comprises a serrated portion and a non-serrated portion. The serrated portion is formed from a plurality of tabs for mixing exhaust gas exiting the flow body with gases passing by an exterior of the flow body. The non-serrated portion is positioned along a lower portion of the trailing edge with respect to the engine centerline.

Abstract: An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a centerline of the engine. The trailing edge comprises a serrated portion and a non-serrated portion. The serrated portion is formed from a plurality of tabs for mixing exhaust gas exiting the flow body with gases passing by an exterior of the flow body. The non-serrated portion is positioned along a lower portion of the trailing edge with respect to the engine centerline.

Abstract: A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.

Abstract: A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.