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A method for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in

A method for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector. The fuel flow control apparatus further includes: at least one sensor for detecting dynamic pressure in the combustor; a fuel nozzle; and, a system for controlling fuel flow supplied by the fuel nozzle through the valves. The fuel nozzle includes: a feed strip with a plurality of circuits for providing fuel to the pilot mixer and the main mixer; and, a plurality of valves associated with the fuel nozzle and in flow communication with the feed strip thereof. The control system activates the valves in accordance with signals received from the pressure sensor.

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1. A method of actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, said mixer assembly including a pilot mixer and a main mixer, wherein said pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mou

1. A method of actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, said mixer assembly including a pilot mixer and a main mixer, wherein said pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in said pilot housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing and a plurality of secondary fuel injection ports for introducing fuel radially inward into said hollow interior of said pilot housing, said method comprising the following steps: (a) continuously sensing dynamic pressure in a combustion chamber of said combustor;(b) determining whether an amplitude of the sensed dynamic pressure in said combustion chamber is greater than a predetermined amount; and,(c) signaling a fuel nozzle to provide fuel to said pilot mixer when said pressure amplitude is greater than said predetermined amount. 2. The method of claim 1, further comprising the step of providing increased fuel flow to said primary fuel injector of said pilot mixer. 3. The method of claim 1, further comprising the step of pulsing fuel through said primary fuel injector of said pilot mixer. 4. The method of claim 1, further comprising the step of providing increased fuel flow to said secondary fuel injection ports of said pilot mixer. 5. The method of claim 1, further comprising the step of pulsing fuel through said secondary fuel injection ports of said pilot mixer. 6. The method of claim 1, wherein said predetermined amount is a pressure amplitude of at least approximately 0.5 psi peak to peak. 7. The method of claim 1, further comprising the step of continuously providing fuel to said primary fuel injector. 8. The method of claim 1, further comprising the step of modifying a rate of fuel provided to said primary fuel injector. 9. A method of actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, said mixer assembly including a pilot mixer and a main mixer, wherein said pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in said pilot housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing and a plurality of secondary fuel injection ports for introducing fuel radially inward into said hollow interior of said pilot housing, said method comprising the following steps: (a) continuously sensing dynamic pressure in a combustion chamber of said combustor;(b) determining whether a frequency of the sensed dynamic pressure in said combustion chamber is within a predetermined range; and,(c) signaling a fuel nozzle to provide fuel to said pilot mixer when said pressure frequency is within said predetermined range. 10. The method of claim 9, further comprising the step of providing increased fuel flow to said primary fuel injector. 11. The method of claim 9, further comprising the step of pulsing fuel through said primary fuel injector of said pilot mixer. 12. The method of claim 9, further comprising the step of providing increased fuel flow to said secondary fuel injection ports of said pilot mixer. 13. The method of claim 9, further comprising the step of pulsing fuel through said secondary fuel injection ports of said pilot mixer. 14. The method of claim 9, wherein said predetermined frequency range is approximately 40 Hertz to approximately 50 Hertz. 15. The method of claim 9, wherein pressure frequency within said predetermined range is indicative of incipient lean blow out in said combustion chamber. 16. The method of claim 9, further comprising the step of continuously providing fuel to said primary fuel injector. 17. The method of claim 9, further comprising the step of modifying a rate of fuel provided to said primary fuel injector. 18. A method of actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor during a plurality of operational stages, said mixer assembly including a pilot mixer and a main mixer, wherein said pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in said pilot housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing, and a plurality of secondary fuel injection ports for introducing fuel radially inward into said hollow interior of said pilot housing, said method comprising the following steps: (a) supplying fuel only to said primary fuel injector and said secondary fuel injection ports of said pilot mixer during a first fueling mode;(b) supplying fuel to said pilot mixer and said main mixer in a first specified amount during a second fueling mode; and,(c) supplying fuel to said pilot mixer and said main mixer in a second specified amount during a third fueling mode. 19. The method of claim 18, wherein said first fueling mode is used to obtain a temperature range of approximately 200° F. to approximately 825° F. in said combustor. 20. The method of claim 18, wherein duration of said first fueling mode is determined by a limit of a pump supplying fuel to said mixer assembly. 21. The method of claim 18, wherein said second fueling mode is used to obtain a temperature range of approximately 825° F. to approximately 950° F. in said combustor. 22. The method of claim 18, wherein approximately 80% of said fuel is supplied to said main mixer and approximately 20% of said fuel is supplied to said pilot mixer during said second fueling mode. 23. The method of claim 18, wherein said second fueling mode is limited by a lean blow out limit at a first end and a limit of a pump supplying fuel to said mixer assembly at a second end. 24. The method of claim 18, wherein said third fueling mode is used to obtain a temperature range of approximately 950° F. to approximately 1125° F. in said combustor. 25. The method of claim 18, wherein approximately 92% of said fuel is provided to said main mixer and approximately 8% of said fuel is provided to said pilot mixer during said third fueling mode. 26. The method of claim 18, wherein said third fueling mode is limited by a lean blow out limit at a first end and a limit of a pump supplying fuel to said mixer assembly at a second end. 27. The method of claim 18, wherein said first fueling mode is used during idle, taxi and approach portions of an operating envelope for said gas turbine engine. 28. The method of claim 18, wherein said second fueling mode is used during climb and cruise portions of an operating envelope for said gas turbine engine. 29. The method of claim 18, wherein said third fueling mode is used during a take-off portion of an operating envelope for said gas turbine engine.