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A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacel

A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.

대표청구항 ▼

1. A turbofan engine control system comprising: a core nacelle housing a compressor and a turbine;a turbofan arranged upstream from the core nacelle and surrounded by a fan nacelle;a bypass flow path downstream from the turbofan and arranged between the core and fan nacelles, the bypass flow path in

1. A turbofan engine control system comprising: a core nacelle housing a compressor and a turbine;a turbofan arranged upstream from the core nacelle and surrounded by a fan nacelle;a bypass flow path downstream from the turbofan and arranged between the core and fan nacelles, the bypass flow path including a nozzle exit area;a controller programmed to detect at least one of a take-off condition and a landing condition, the controller programmed to effectively alter the nozzle exit area to change a thrust vector in response to the at least one of the take-off and the landing conditions; andwherein the core nacelle includes a low spool supporting the compressor and turbine, the low spool for rotationally driving the turbofan through an epicyclic gear train. 2. The turbofan engine control system according to claim 1, wherein the landing condition includes initiation of a landing. 3. The turbofan engine control system according to claim 1, wherein the core nacelle includes a high spool supporting a high pressure compressor and a high pressure turbine. 4. The turbofan engine control system according to claim 1, comprising a flow control device including an actuator for changing the nozzle exit area physically in response to the at least one of the take-off and the landing conditions. 5. The turbofan engine control system according to claim 4, wherein the flow control device includes flaps movable in response to the actuator to change the thrust vector. 6. The turbofan engine control system according to claim 5, wherein a geometry of the nozzle exit area is changed in response to the at least one of the take-off and the landing conditions. 7. The turbofan engine control system according to claim 1, wherein the take-off condition includes a maximum take-off throttle. 8. The turbofan engine control system according to claim 3, wherein the gear train includes a gear reduction ratio greater than 2.5:1. 9. The turbofan engine control system according to claim 7, wherein the controller is programmed to discontinue the thrust vector in response to an aircraft achieving a predetermined velocity. 10. The turbofan engine control system according to claim 3, wherein the high and low spool and the turbofan provide a bypass ratio that is greater than 10:1. 11. The turbofan engine control system according to claim 3, wherein the turbine of the low spool includes a pressure ratio that is greater than 5:1. 12. The turbofan engine control system according to claim 2, wherein the controller is programmed to discontinue the thrust vector in response to a command manually by a pilot. 13. The turbofan engine control system according to claim 2, wherein the initiation of the landing includes engagement of full flaps down. 14. A method of controlling a turbofan engine having a fan that is rotationally driven by an epicyclic gear train comprising the steps of: a) determining at least one of a take-off condition and a landing condition;b) effectively altering a turbofan bypass flow nozzle exit area in response to performing step a);c) changing a thrust vector for the at least one of the take-off and the landing conditions; andd) discontinuing the changed thrust vector in response to an aircraft achieving a predetermined velocity. 15. The method according to claim 14, wherein step a) includes sensing a maximum take-off throttle. 16. The method according to claim 14, wherein step a) includes initiating a landing. 17. The method according to claim 16, wherein step a) includes engaging full flaps. 18. The method according to claim 16, comprising step d) manually discontinuing the thrust vector. 19. The method according to claim 14, wherein step b) includes changing the nozzle exit area physically in response to the at least one of the take-off and the landing conditions. 20. The method according to claim 14, wherein steps a) through d) are performed by a controller programmed to detect at least one of a take-off condition and a landing condition and to effectively alter the nozzle exit area.