초록 ▼

A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at least one flow boundary surface t

A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at least one flow boundary surface to facilitate attenuating noise generated during engine operation.

대표청구항 ▼

What is claimed is: 1. A method for operating a gas turbine engine, said method comprising: channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface; and selectively operating a noise suppression system extending from the at least one flow

What is claimed is: 1. A method for operating a gas turbine engine, said method comprising: channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface; and selectively operating a noise suppression system extending from the at least one flow boundary surface to facilitate attenuating noise generated during engine operation by injecting air into a stream flow from the at least one flow boundary surface to form streamwise vortices. 2. A method in accordance with claim 1 wherein channeling exhaust gases from a core engine further comprises: channeling a flow through a core stream passageway defined between a core cowl and an engine centerbody; and injecting air from said noise suppression system inwardly into the core stream passageway. 3. A method in accordance with claim 1 wherein channeling exhaust gases from a core engine further comprises: channeling a flow through a bypass stream passageway defined between an annular core nozzle and an annular fan nozzle; and injecting air from said noise suppression system inwardly into the bypass stream passageway. 4. A method in accordance with claim 1 wherein channeling exhaust gases from a core engine further comprises injecting air from said noise suppression system inwardly into the external stream flow flowing past the gas turbine engine. 5. An assembly for a gas turbine engine, said assembly comprising: a centerbody; a fan nozzle assembly having an outer case; a fan nozzle radially outwardly from said centerbody, at least one of said fan nozzle and said centerbody comprises a flow boundary; and a noise suppression system extending from at least one of said fan assembly outer case and said centerbody, said noise suppression system selectively operable during engine operations to facilitate attenuating jet noise generated during engine operation and configured to inject air from at least one flow boundary surface and generate streamwise vortices into at least one of a bypass stream flow and a freestream flowing past said assembly. 6. An assembly in accordance with claim 5 wherein said noise suppression system comprises at least one synthetic jet actuator. 7. An assembly in accordance with claim 5 wherein said flow boundary comprises a radially outer surface of at least one of said centerbody and said fan nozzle. 8. An assembly in accordance with claim 5 further comprising an annular core nozzle spaced radially outwardly from said centerbody, said flow boundary comprises a radially inner surface of said core nozzle, said noise suppression system is configured to inject air into a core stream passageway defined between said annular core nozzle and the centerbody. 9. An exhaust assembly in accordance with claim 5 wherein said flow boundary comprises a radially inner surface of said fan nozzle, said noise suppression system is configured to inject air into a bypass stream passageway defined between said fan nozzle and the annular core nozzle. 10. An assembly in accordance with claim 5 wherein said annular fan nozzle is spaced radially outwardly from an annular core nozzle, said flow boundary comprises a radially outer surface of said fan nozzle, said noise suppression system is configured to inject air into the external stream flow surrounding said fan nozzle. 11. A gas turbine engine comprising: a core engine; and an exhaust assembly extending downstream from said core engine for discharging exhaust gases from said core engine, said exhaust assembly comprising a flow boundary surface and a noise suppression system extending from said flow boundary surface, said noise suppression system is selectively operable to facilitate attenuating noise generated during engine operation by injecting air outwardly from said at least one flow boundary surface to generate streamwise vortices. 12. A gas turbine engine in accordance with claim 11 wherein said exhaust assembly noise suppression system comprises at least one synthetic jet actuator. 13. A gas turbine engine in accordance with claim 11 wherein said exhaust assembly further comprises a centerbody extending aftward from said core engine, said noise suppression system extending from a radially outer surface of said centerbody for injecting air into exhaust gases flowing past said centerbody. 14. A gas turbine engine in accordance with claim 11 wherein said exhaust assembly further comprises a centerbody and an annular core nozzle, said core nozzle spaced radially outwardly from said centerbody such that a core stream passageway is defined therebetween, said noise suppression system for injecting air inwardly into said core stream passageway. 15. A gas turbine engine in accordance with claim 11 wherein said exhaust assembly further comprises a centerbody, an annular core nozzle, and a fan nozzle, said core nozzle spaced radially outwardly from said centerbody such that a core stream passageway is defined therebetween, said fan nozzle spaced radially outwardly from said core nozzle such that a bypass stream passageway is defined therebetween, said noise suppression system for injecting air inwardly into said bypass stream passageway. 16. A gas turbine engine in accordance with claim 11 wherein said exhaust assembly further comprises a centerbody, an annular core nozzle, and a fan nozzle, said core nozzle spaced radially outwardly from said centerbody such that a core stream passageway is defined therebetween, said fan nozzle spaced radially outwardly from said core nozzle such that a bypass stream passageway is defined therebetween, said noise suppression system for injecting air radially outwardly from said fan nozzle into an external stream flow surrounding said fan nozzle. 17. A gas turbine engine in accordance with claim 11 wherein said gas turbine engine comprises at least one of a high bypass ratio turbofan engine and a low bypass ratio turbofan engine.