초록 ▼

A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft s

A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor; receiving a control command from a full authority digital engine control (FADEC) in the control system; generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received; generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; and supplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine.

대표청구항 ▼

1. A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle, the method comprising: receiving into a control system at least one condition input from a respective sensor;receiving into a control system a low pressure shaft speed from

1. A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle, the method comprising: receiving into a control system at least one condition input from a respective sensor;receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor;receiving a control command from a full authority digital engine control (FADEC) in the control system;generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received;generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; andsupplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine. 2. The method as in claim 1, wherein the at least one condition input includes an aircraft speed input from a speed sensor. 3. The method as in claim 1, wherein the at least one condition input includes an engine inlet temperature input from an inlet temperature sensor. 4. The method as in claim 1, wherein the at least one condition input includes an engine inlet pressure input from an inlet pressure sensor. 5. The method as in claim 1, further comprising: generating a high pressure shaft speed base reference from the control command and the at least one condition input from the respective sensor. 6. The method as in claim 5, wherein the engine control system adjusts the fuel flow to the engine based upon the high pressure shaft speed base reference and an input from a high pressure shaft speed sensor. 7. The method as in claim 1, wherein the engine control system adjusts both the fuel flow and the pitch angle. 8. The method as in claim 1, wherein the gas turbine engine includes a plurality of outer guide vanes having a variable pitch angle; the method further comprising: generating an outer guide vane base reference from the at least one condition input received, the control command received, and the beta angle of the blade. 9. The method as in claim 8, further comprising: adjusting the variable pitch angle of the outer guide vanes. 10. The method as in claim 1, wherein the gas turbine engine comprises a variable pitch fan engine, a turbo-shaft engine, or a turbo-propeller engine. 11. The method as in claim 1, further comprising: receiving a fuel flow signal;receiving a pitch change mechanism signal;relating in a controlled plant a pitch change mechanism pitch angle (BetaP) from the pitch change mechanism signal and a fuel flow (Wf) fuel flow signal to at least two controlled outputs, wherein a first one of the controlled outputs is either propeller speed (Nx) or power turbine shaft speed (N1) and a second one of the controlled outputs is engine core speed (N2), engine pressure ratio (EPR) or engine torque (Tq). 12. The method of claim 1, further comprising: performing a transcient schedule in forward thrust to change the beta angle based upon NxC_Ref, NxC, PLA, and Mach. 13. The method of claim 1, further comprising: performing a transcient schedule in reverse thrust to change the beta angle based upon Beta_Ref, Beta, PLA, and Mach. 14. The method of claim 1, further comprising: performing a transcient schedule in ground mode to change the beta angle based upon NxC_Ref, NxC, PLA, and Beta. 15. The method of claim 1, further comprising: performing a transcient schedule in forward thrust to change the low pressure shaft speed and the beta angle based upon NxC_Ref, NxC, PLA, and Mach. 16. The method of claim 1, further comprising: performing a transcient schedule in reverse thrust to change the low pressure shaft speed and the beta angle based upon NxC_Ref, NxC, PLA, and Beta. 17. The method of claim 16, further comprising: performing a transcient schedule in reverse thrust to change the low pressure shaft speed and the beta angle based upon NxC_Ref, NxC, PLA, and Mach.