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A fuel nozzle device suitable for use in a gas turbine engine or the like is provided. The fuel nozzle device includes a fuel line and a plurality of gas orifices disposed at a downstream end of the fuel line, the plurality of gas orifices operable for injecting fuel into an air stream. The acoustic

A fuel nozzle device suitable for use in a gas turbine engine or the like is provided. The fuel nozzle device includes a fuel line and a plurality of gas orifices disposed at a downstream end of the fuel line, the plurality of gas orifices operable for injecting fuel into an air stream. The acoustic resistance of each of the plurality of gas orifices is chosen to match the acoustic impedance of the fuel line such that the maximum acoustic energy may be transferred between the fuel nozzle device and the combustor, thus enhancing the ability of the fuel nozzle device to control the combustion dynamics of the gas turbine engine system. A fuel injection resonator assembly suitable for use in a gas turbine engine or the like is also provided. The fuel injection resonator assembly includes a plurality of orifices separated by a variable length tube. The area ratio of the plurality of orifices may be adjusted using an automated valve system or the like to modify and/or control the relative flow resistance of the plurality of orifices. The resulting fuel injection resonator assembly acts as a tunable acoustic waveguide operable for delivering fuel to the combustor.

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1. A fuel nozzle device operable for injecting a fuel into an air stream and suitable for use in a gas turbine engine system or the like, the fuel nozzle device comprising:an orifice portion having a first cross-sectional area, A h , and a first acoustic impedance, Z 1 ;a tube portion having a seco

1. A fuel nozzle device operable for injecting a fuel into an air stream and suitable for use in a gas turbine engine system or the like, the fuel nozzle device comprising:an orifice portion having a first cross-sectional area, A h , and a first acoustic impedance, Z 1 ;a tube portion having a second cross-sectional area, A T , and a second acoustic impedance, Z 2 ; andwherein the ratio of the first cross-sectional area, A h , of the orifice portion and the second cross-sectional area, A T , of the tube portion is selected such that the first acoustic impedance, Z 1 , of the orifice portion is substantially the same as the second acoustic impedance, Z 2 , of the tube portion. 2. The fuel nozzle device of claim 1, wherein the orifice portion comprises a plurality of orifices each having a first cross-sectional area, A h , and a first acoustic impedance, Z 1 . 3. The fuel nozzle device of claim 2, wherein the ratio of the first cross-sectional area, A h , of each of the plurality of orifices and the second cross-sectional area, A T , of the tube portion is selected such that the first acoustic impedance, Z 1 , of each of the plurality of orifices is substantially the same as the second acoustic impedance, Z 2 , of the tube portion. 4. The fuel nozzle device of claim 1, wherein the ratio of the first cross-sectional area, A h , of the orifice portion and the second cross-sectional area, A T , of the tube portion is expressed by the equation:wherein dp % comprises a predetermined pressure drop, C D comprises a discharge coefficient of the orifice portion, and γ comprises a predetermined characteristic of the fuel. 5. The fuel nozzle device of claim 1, wherein the tube portion comprises a fuel line. 6. The fuel nozzle device of claim 1, wherein the first cross-sectional area, A h , of the orifice portion is adjustable. 7. The fuel nozzle device of claim 1, wherein the second cross-sectional area, A T , of the tube portion is adjustable. 8. The fuel nozzle device of claim 1, wherein the air stream is disposed within a combustion device. 9. The fuel nozzle device of claim 1, wherein Z 1 and Z 2 comprise values between 0.52 and 1.92. 10. A method for controlling the combustion dynamics of a gas turbine engine system or the like, the method comprising:providing an orifice portion having a first cross-sectional area, A h , and a first acoustic impedance, Z 1 ;providing a tube portion having a second cross-sectional area, A T , and a second acoustic impedance, Z 2 ; andselecting the ratio of the first cross-sectional area, A h , of the orifice portion and the second cross-sectional area, A T , of the tube portion such that the first acoustic impedance, Z 1 , of the orifice portion is substantially the same as the second acoustic impedance, Z 2 , of the tube portion. 11. The method of claim 10, wherein the orifice portion comprises a plurality of orifices each having a first cross-sectional area, A h , and a first acoustic impedance, Z 1 . 12. The method of claim 11, wherein selecting the ratio of the first cross-sectional area, A h , of the orifice portion and the second cross-sectional area, A T , of the tube portion such that the first acoustic impedance, Z 1 , of the orifice portion is substantially the same as the second acoustic impedance, Z 2 , of the tube portion comprises selecting the ratio of the first cross-sectional area, A h , of each of the plurality of orifices and the second cross-sectional area, A T , of the tube portion such that the first acoustic impedance, Z 1 , of each of the plurality of orifices is substantially the same as the second acoustic impedance, Z 2 , of the tube portion. 13. The method of claim 10, wherein the ratio of the first cross-sectional area, A h , of the orifice portion and the second cross-sectional area, A T , of the tube portion is expressed by the equation:wherein dp % comprises a predetermined pressure drop, C D comprises a discharge coefficient of the orifi ce portion, and γ comprises a predetermined characteristic of a fuel. 14. The method of claim 10, wherein providing the tube portion comprises providing a fuel line. 15. The method of claim 10, further comprising adjusting the first cross-sectional area, A h , of the orifice portion. 16. The method of claim 10, further comprising adjusting the second cross-sectional area, A T , of the tube portion. 17. A fuel injection resonator assembly operable for injecting a fuel into an air stream and suitable for use in a gas turbine engine system or the like, the fuel injection resonator assembly comprising:a tube portion operable for containing and transporting the fuel, wherein the tube portion comprises an upstream end and a downstream end, and wherein the length of the tube portion is adjustable;a plurality of upstream orifices operable for delivering the fuel to the air stream, wherein the plurality of upstream orifices are disposed about the upstream end of the tube portion;a plurality of downstream orifices operable for delivering the fuel to the air stream, wherein the plurality of downstream orifices are disposed about the downstream end of the tube portion; andwherein the length of the tube portion is selected during operation to avoid or achieve assembly resonance in a predetermined range. 18. The fuel injection resonator assembly of claim 17, wherein the tube portion comprises an annular chamber. 19. The fuel injection resonator assembly of claim 17, wherein the tube portion comprises a plurality of tubes. 20. The fuel injection resonator assembly of claim 17, wherein the cross-sectional area of each of the plurality of upstream orifices is adjustable. 21. The fuel injection resonator assembly of claim 20, wherein the cross-sectional area of each of the plurality of upstream orifices is selected to avoid or achieve assembly resonance in a predetermined range. 22. The fuel injection resonator assembly of claim 17, wherein the cross-sectional area of each of the plurality of downstream orifices is adjustable. 23. The fuel injection resonator assembly of claim 22, wherein the cross-sectional area of each of the plurality of downstream orifices is selected to avoid or achieve assembly resonance in a predetermined range. 24. The fuel injection resonator assembly of claim 17, further comprising a tunable acoustic resonator device in communication with the tube portion, wherein the tunable acoustic resonator device is operable for applying a resonant frequency to the tube portion. 25. The fuel injection resonator assembly of claim 24, wherein the resonant frequency of the tunable acoustic resonator device is selected to avoid or achieve assembly resonance in a predetermined range. 26. The method of claim 24, wherein the tunable acoustic resonator device is a Helmholtz resonator. 27. The fuel injection resonator assembly of claim 17, wherein the air stream is disposed within a combustion device. 28. A fuel injection resonator assembly operable for injecting a fuel into an air stream and suitable for use in a gas turbine engine system or the like, the fuel injection resonator assembly comprising:a tube portion operable for containing and transporting the fuel, wherein the tube portion comprises an upstream end and a downstream end, and wherein the length of the tube portion is adjustable;a plurality of upstream orifices operable for delivering the fuel to the air stream, wherein the plurality of upstream orifices are disposed about the upstream end of the tube portion, and wherein the cross-sectional area of each of the plurality of upstream orifices is adjustable;a plurality of downstream orifices operable for delivering the fuel to the air stream, wherein the plurality of downstream orifices are disposed about the downstream end of the tube portion;wherein the length of the tube portion is selected during operation to avoid or achieve assembly resonance in a predetermined range; andwherein the cross-sectional area of each o f the plurality of upstream orifices is selected during operation to avoid or achieve assembly resonance in a predetermined range. 29. The fuel injection resonator assembly of claim 28, wherein the tube portion comprises an annular chamber. 30. The fuel injection resonator assembly of claim 28, wherein the tube portion comprises a plurality of tubes. 31. The fuel injection resonator assembly of claim 28, wherein the cross-sectional area of each of the plurality of downstream orifices is adjustable. 32. The fuel injection resonator assembly of claim 31, wherein the cross-sectional area of each of the plurality of downstream orifices is selected to avoid or achieve assembly resonance in a predetermined range. 33. The fuel injection resonator assembly of claim 28, further comprising a tunable acoustic resonator device in communication with the tube portion, wherein the tunable acoustic resonator device is operable for applying a resonant frequency to the tube portion. 34. The fuel injection resonator assembly of claim 33, wherein the resonant frequency of the tunable acoustic resonator device is selected to avoid or achieve assembly resonance in a predetermined range. 35. The method of claim 33, wherein the tunable acoustic resonator device is a Helmholtz resonator. 36. The fuel injection resonator assembly of claim 28, wherein the air stream is disposed within a combustion device. 37. A method for controlling the combustion dynamics of a gas turbine engine system or the like, the method comprising:providing a tube portion operable for containing and transporting a fuel, wherein the tube portion comprises an upstream end and a downstream end, and wherein the length of the tube portion is adjustable;providing a plurality of upstream orifices operable for delivering the fuel to an air stream, wherein the plurality of upstream orifices are disposed about the upstream end of the tube portion, and wherein the cross-sectional area of each of the plurality of upstream orifices is adjustable;providing a plurality of downstream orifices operable for delivering the fuel to the air stream, wherein the plurality of downstream orifices are disposed about the downstream end of the tube portion;selecting the length of the tube portion during operation to avoid or achieve resonance of the tube portion, the plurality of upstream orifices, and the plurality of downstream orifices in a predetermined range; andselecting the cross-sectional area of each of the plurality of upstream orifices during operation to avoid or achieve resonance of the tube portion, the plurality of upstream orifices, and the plurality of downstream orifices in a predetermined range. 38. The method of claim 37, wherein providing the tube portion comprises providing an annular chamber. 39. The method of claim 37, wherein providing the tube portion comprises providing a plurality of tubes. 40. The method of claim 37, wherein the cross-sectional area of each of the plurality of downstream orifices is adjustable. 41. The method of claim 40, further comprising selecting the cross-sectional area of each of the plurality of downstream orifices to avoid or achieve resonance of the tube portion, the plurality of upstream orifices, and the plurality of downstream orifices in a predetermined range. 42. The method of claim 37, further comprising providing a tunable acoustic resonator device in communication with the tube portion, wherein the tunable acoustic resonator device is operable for applying a resonant frequency to the tube portion. 43. The method of claim 42, further comprising selecting the resonant frequency of the tunable acoustic resonator device to avoid or achieve resonance of the tube portion, the plurality of upstream orifices, and the plurality of downstream orifices in a predetermined range. 44. The method of claim 42, wherein the tunable acoustic resonator device is a Helmholtz resonator.