Gas turbine engine variable area fan nozzle control

• US 10,006,406 B2
• Filed: 09/30/2014
• Issued: 06/26/2018
• Est. Priority Date: 01/31/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Blackwell, Geoffrey T., McVey, William J., Tempelman, William G.
• Primary Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US14/502,354
• Publication Number:
  US 20150315976A1
• Time in Patent Office: 1,365 Days
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 9/16 Control of working fluid flow F02C9/48 takes precedence; control of air-intake flow F02C7/057
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02K 1/06 Varying effective area of jet pipe or nozzle by using fluid jets to influence the jet flow F02K1/30
• CPC Class Codes: F02K 1/09 by axially moving an external member, e.g. a shroud F02K1/12 takes precedence
• CPC Class Codes: F02K 1/18 automatic
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2270/101 Compressor surge or stall
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/3061 of the working fluid

Abstract

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.

Claims

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; and

adjusting 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; and

a 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; and

a 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; and

a 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.