[특허]Gas turbine engine variable area fan nozzle control

Gas turbine engine variable area fan nozzle control 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/06 F02C-009/16 F02K-001/06 F02K-001/09 F02K-001/18 F02C-003/107 F02C-009/18 F02C-009/28
출원번호	US-0502354 (2014-09-30)
등록번호	US-10006406 (2018-06-26)
발명자 / 주소	Blackwell, Geoffrey T. McVey, William J. Tempelman, William G.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 36

초록 ▼

A method of managing a gas turbine engine includes the steps of detecting an airspeed and detecting a fan speed. A parameter relationship is referenced related to a desired variable area fan nozzle position based upon at least airspeed and fan speed. The detected airspeed and detected fan speed is compared to the parameter relationship to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted in response to the determination of the target area fan nozzle position and at least one threshold.

대표청구항 ▼

1. A method of managing a gas turbine engine comprising the steps of: detecting an airspeed;detecting a fan speed;referencing a parameter relationship related to a desired variable area fan nozzle position based upon at least airspeed and fan speed, the parameter relationship includes at least one of first and second thresholds respectively corresponding to upper and lower fan speed limits that provide a schedule of curves of the fan speed in relation to a fan aerodynamic design speed, wherein the upper and lower fan speed limits are less than the fan aerodynamic design speed, and comparing the detected airspeed and detected fan speed to the parameter relationship to determine a target variable area fan nozzle position according to the schedule of curves; andadjusting an actual variable area fan nozzle position to the target variable area fan nozzle position. 2. The method according to claim 1, wherein the fan speed detecting step includes detecting a low speed spool rotational speed, and correcting the fan speed based upon an ambient temperature. 3. The method according to claim 2, wherein the fan speed detecting step includes calculating the fan speed based upon a gear reduction ratio. 4. The method according to claim 1, wherein the referencing and comparing steps include providing the target variable area fan nozzle position for a range of air speeds based upon the fan speed. 5. The method according to claim 4, wherein the air speed range is 0.35-0.55 Mach, and a data table includes the first and second thresholds. 6. The method according to claim 5, wherein the lower fan speed limit is 60% of the fan aerodynamic design speed, and the upper fan speed limit is 75% of the fan aerodynamic design speed. 7. The method according to claim 5, wherein the lower fan speed limit is 65% of the fan aerodynamic design speed. 8. The method according to claim 5, wherein the upper fan speed limit is 75% of the fan aerodynamic design speed. 9. The method according to claim 1, wherein the adjusting step includes adjusting the target variable fan nozzle position to provide an exit area of a fan nacelle. 10. The method according to claim 9, wherein the adjusting step includes translating flaps to selectively block a vent in the fan nacelle. 11. The method according to claim 1, wherein the gas turbine engine comprises: a fan arranged in a fan nacelle including a flap configured to be movable between first and second positions;an actuator operatively coupled to the flap;a compressor section fluidly connected to the fan, the compressor comprising a high pressure compressor and a low pressure compressor;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising: a high pressure turbine coupled to the high pressure compressor via a shaft; anda low pressure turbine. 12. The method according to claim 11, wherein the gas turbine engine includes a low Fan Pressure Ratio of less than about 1.45. 13. A gas turbine engine comprising: fan nacelle including a flap configured to be movable between first and second positions;an actuator operatively coupled to the flap; anda controller configured to reference a parameter relationship that relates to a desired variable area fan nozzle position based upon at least airspeed and fan speed, the controller configured to compare a detected airspeed and a detected fan speed to the parameter relationship to determine a target variable area fan nozzle position, the parameter relationship includes at least one of first and second thresholds respectively corresponding to lower and upper fan speed limits that provide a schedule of curves of the fan speed in relation to a fan aerodynamic design speed, wherein the upper and lower fan speed limits are less than the fan aerodynamic design speed, and the controller configured to provide a command to the actuator to adjust the flap from the first position to the second position corresponding to the target variable fan nozzle position, the target variable area fan nozzle position selected according to the schedule of curves. 14. The gas turbine engine according to claim 13, comprising: a fan arranged in the fan nacelle;a compressor section fluidly connected to the fan, the compressor comprising a high pressure compressor and a low pressure compressor;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising: a high pressure turbine coupled to the high pressure compressor via a shaft; anda low pressure turbine. 15. The gas turbine engine according to claim 14, wherein the gas turbine engine includes a low Fan Pressure Ratio of less than about 1.45. 16. The gas turbine engine according to claim 13, wherein the controller is configured to provide the target variable area fan nozzle position for a range of air speeds based upon the fan speed, the air speed range is 0.35-0.55 Mach, and a data table includes the first and second thresholds corresponding to the lower and upper fan speed limits, the target variable area fan nozzle position selected based upon the first and second thresholds.

이 특허에 인용된 특허 (36)

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Shah,Anil D.; Gupta,Alankar, Method and apparatus for detecting conditions conducive to ice formation.
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Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT), Nacelle and mounting arrangement for an aircraft engine.
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McCarty Frederick B. (San Pedro CA) Fitzgibbon Thomas F. (Long Beach CA), Quad mode fan pitch actuation system for a gas turbine engine.
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Giffin ; III Rollin G. (Cincinnati OH), Variable specific thrust turbofan engine.
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