초록 ▼

A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct.

A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct. A first member couples the nacelle to the core cowl and includes a first flap hingedly coupled to each sidewall of the first member. An opposing second member couples the nacelle to the core cowl and includes a second flap hingedly coupled to each sidewall of the second member. The first flaps and the second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct. A turbofan engine assembly and a method for operating the same are also provided.

대표청구항 ▼

What is claimed is: 1. A method for operating a turbofan engine assembly including a core gas turbine engine, said method comprising: varying an operating speed of the turbofan engine assembly from a first operating speed to a second operating speed; and selectively positioning at least one of a fi

What is claimed is: 1. A method for operating a turbofan engine assembly including a core gas turbine engine, said method comprising: varying an operating speed of the turbofan engine assembly from a first operating speed to a second operating speed; and selectively positioning at least one of a first set of flaps and a second set of flaps to vary a throat area of a fan nozzle duct defined downstream from the core gas turbine engine, wherein the first set of flaps and the second set of flaps are coupled downstream from the core gas turbine engine and inside the fan nozzle duct, wherein at least one flap of said first set of flaps are longer than at least one flap of said second set of flaps. 2. A method in accordance with claim 1 wherein selectively positioning at least one of a first set of flaps and a second set of flaps further comprises positioning each of the first set of flaps and each of the second set of flaps at an angle. 3. A method in accordance with claim 1 wherein selectively positioning at least one of a first set of flaps and a second set of flaps further comprises positioning each flap to increase the throat area of fan nozzle duct. 4. A method in accordance with claim 1 wherein selectively positioning at least one of a first set of flaps and a second set of flaps further comprises positioning each flap at an angle with respect to a centerline extending through the turbofan engine assembly, wherein the angle is from about 0° to about 20°. 5. A method in accordance with claim 1 wherein selectively positioning at least one of a first set of flaps and a second set of flaps further comprises positioning each flap of the first set of flaps at a first angle with respect to a centerline extending through the turbofan engine assembly wherein the first angle is from about 0° to about 20°, and positioning each flap of the second set of flaps at a second angle with respect to the centerline wherein the angle is from about 0° to about 10°. 6. A nozzle assembly for a gas turbine aircraft engine, said nozzle assembly comprising: a nacelle; a core cowl positioned at least partially within said nacelle such that said core cowl and said nacelle are aligned substantially concentrically to each other such that an annular fan bypass duct is defined between said nacelle and said core cowl; a first member coupling said nacelle to said core cowl, said first member comprising opposing sidewalls and a first flap hingedly coupled to each of said first member sidewalls; a second member opposite said first member and coupling said nacelle to said core cowl, said second member comprising opposing sidewalls and a second flap hingedly coupled to each of said second member sidewalls, wherein said first flaps and said second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct, wherein said first flaps of said first member are longer than said second flaps of said second member. 7. A nozzle assembly in accordance with claim 6 wherein said first member and said second member are aligned substantially coplanarly with respect to each other and divide said fan bypass duct into two duct portions that have substantially the same flow area. 8. A nozzle assembly in accordance with claim 6 wherein each flap of said first flaps and said second flaps are selectively positionable at an angle from about 0° to about 20° measured with respect to a centerline extending through the gas turbine aircraft engine. 9. A nozzle assembly in accordance with claim 6 wherein each of said first and second members has a width, the width of said second member is smaller than said first member width. 10. A nozzle assembly in accordance with claim 6 wherein said nozzle assembly further comprises a plurality of actuators, each said actuator couples one of said flaps to said corresponding sidewall. 11. A nozzle assembly in accordance with claim 10 wherein each actuator includes an actuating mechanism and an extending rod connecting said actuating mechanism to a link, such that energizing said actuating mechanism facilitates moving said flap. 12. A turbofan engine assembly comprising: a core gas turbine engine; a nacelle; a core cowl positioned at least partially within said nacelle such that said core cowl and said nacelle are aligned substantially concentrically to each other such that an annular fan bypass duct is defined between said nacelle and said core cowl; a first member coupling said nacelle to said core cowl, said first member comprising opposing sidewalls and a first flap hingedly coupled to each of said first member sidewalls; and a second member opposite said first member and coupling said nacelle to said core cowl, said second member comprising opposing sidewalls and a second flap hingedly coupled to each of said second member sidewalls, wherein said first flaps and said second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct, wherein wherein said first flap of said first member are longer than said second flap of said second member. 13. A turbofan engine assembly in accordance with claim 12 wherein said first member and said second member are aligned substantially coplanarly with respect to each other and divide said fan bypass duct into two duct portions that have substantially the same flow area. 14. A turbofan engine assembly in accordance with claim 12 wherein each flap of said first flaps and said second flaps are selectively positionable at an angle from about 0° to about 20° measured with respect to a centerline extending through the turbofan engine assembly. 15. A turbofan engine assembly in accordance with claim 12 wherein each of said first and second members includes a width, the width of said second member is smaller than said first member width. 16. A turbofan engine assembly in accordance with claim 12 wherein said turbofan engine assembly further comprises a plurality of actuators, each said actuator couples one of said flaps to said corresponding sidewall.