초록 ▼

A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inne

A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.

대표청구항 ▼

What is claimed is: 1. A method for operating a turbofan engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and a

What is claimed is: 1. A method for operating a turbofan engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and a first core cowl baffle positioned within the fan nozzle duct and a second core cowl baffle wherein a portion of the second core cowl baffle is repositionable with respect to the first core cowl baffle, said method comprising: varying an operating speed of the fan assembly from a first operating speed to a second operating speed; and selectively positioning a portion of the second core cowl baffle between a first operational position and a second operational position with respect to the first core cowl baffle to vary a throat area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed. 2. A method in accordance with claim 1 wherein selectively positioning a portion of the second core cowl baffle further comprises positioning the second core cowl baffle substantially flush against a portion of the core cowl to facilitate maximizing engine thrust. 3. A method in accordance with claim 1 wherein selectively positioning a portion of the second core cowl baffle further comprises positioning a portion of the second core cowl baffle a distance away from the core cowl to facilitate maximizing engine efficiency. 4. A method in accordance with claim 3 wherein selectively positioning a portion of the second core cowl baffle further comprises positioning a portion of the second core cowl baffle a distance away from the core cowl such that a portion of the second core cowl baffle is radially aligned with a portion of the first core cowl baffle to facilitate maximizing engine efficiency. 5. A method in accordance with claim 1 wherein selectively positioning a portion of the second core cowl baffle further comprises positioning the second core cowl baffle a distance away from the core cowl to facilitate maintaining fan efficiency. 6. A method in accordance with claim 1 wherein said method further comprises axially translating the core cowl baffle in a forward direction such that the fan nozzle duct throat area is reduced. 7. A method in accordance with claim 1 wherein at least one of the first core cowl baffle and the second core cowl baffle comprises at least one noise reduction panel, said method further comprising positioning a portion of the second core cowl baffle in at least one of the first operational position and the second operational position to direct the airflow through the fan nozzle duct to facilitate reducing noise using the at least one noise reduction panel. 8. An inner core cowl baffle assembly for a turbofan engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle, said inner core cowl baffle assembly comprising: a first core cowl baffle coupled to a portion of said core cowl within said fan nozzle duct; a second core cowl baffle coupled to a portion of said core cowl and positioned a distance radially inward from said first core cowl baffle; and an actuator assembly configured to vary the throat area of said fan nozzle duct by selectively repositioning said second core cowl baffle with respect to said first core cowl baffle. 9. An inner core cowl baffle assembly in accordance with claim 8 wherein said first and second core cowl baffle are positioned within the fan nozzle duct. 10. An inner core cowl baffle assembly in accordance with claim 8 wherein said actuator assembly is positioned within a portion of said core cowl and is configured to couple said core cowl baffle to said core cowl. 11. An inner core cowl baffle assembly in accordance with claim 9 wherein said actuator assembly comprises a plurality of circumferentially-spaced apart motors, and a plurality of extending rods, each of said plurality of rods is coupled to a respective motor such that actuating at least one of said motors causes a portion of said second core cowl baffle to be translated. 12. An inner core cowl baffle assembly in accordance with claim 9 wherein said actuator assembly is at least one of electrically, pneumatically, or hydraulically powered. 13. An inner core cowl baffle assembly in accordance with claim 8 wherein said actuator assembly repositions a portion said second inner core cowl baffle between a first operational position, a second operational position, and a plurality of operational positions between said first and second operational positions. 14. An inner core cowl baffle assembly in accordance with claim 13 wherein said second inner core cowl baffle is positioned substantially flush with said core cowl in said first operational position, said first operational position facilitates enhancing engine thrust generated from said engine assembly. 15. An inner core cowl baffle assembly in accordance with claim 13 wherein said second inner core cowl baffle is positioned a distance away from said core cowl in said second operational position such that said second operational position facilitates maximizing engine efficiency when the engine assembly is operated a thrust level that is less than maximum thrust. 16. An inner core cowl baffle assembly in accordance with claim 8 wherein said first core cowl baffle is coupled to said core cowl with at least one strut. 17. An inner core cowl baffle assembly in accordance with claim 8 wherein at least one of said first core cowl baffle and said second core cowl baffle includes at least one fixed noise reduction panel. 18. A turbofan engine assembly comprising: a core gas turbine engine; a core cowl which circumscribes said core gas turbine engine; a nacelle positioned radially outward from said core cowl; a fan nozzle duct defined between said core cowl and said nacelle; and an inner core cowl baffle assembly positioned within said fan nozzle duct comprising: a first core cowl baffle coupled to a portion of said core cowl within said fan nozzle duct; a second core cowl baffle coupled to a portion of said core cowl and positioned a distance radially inward from said first core cowl baffle; and an actuator assembly configured to vary the throat area of said fan nozzle duct by selectively repositioning said second core cowl baffle with respect to said first core cowl baffle. 19. A turbofan engine assembly in accordance with claim 18 wherein said second core cowl baffle includes a first portion and a second portion such that said second portion is upstream from said first portion, said second portion is repositionable with respect to said core cowl and said first portion. 20. A turbofan engine assembly in accordance with claim 18 wherein said first core cowl baffle is coupled to said core cowl with at least one strut.