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Methods and systems for combustion dynamics reduction are provided. A combustion chamber may include a first premixer and a second premixer. Each premixer may include at least one fuel injector, at least one air inlet duct, and at least one vane pack for at least partially mixing the air from the ai

Methods and systems for combustion dynamics reduction are provided. A combustion chamber may include a first premixer and a second premixer. Each premixer may include at least one fuel injector, at least one air inlet duct, and at least one vane pack for at least partially mixing the air from the air inlet duct or ducts and fuel from the fuel injector or injectors. Each vane pack may include a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air may pass. The vane pack or packs of the first premixer may be positioned at a first axial position and the vane pack or packs of the second premixer may be positioned at a second axial position axially staggered with respect to the first axial position.

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What is claimed is: 1. A combustion chamber for a gas turbine engine, comprising: a first premixer and a second premixer oriented about an axis defined between an upstream end and a downstream end of a combustor, each premixer comprising at least one fuel injector, at least one air inlet duct, and

What is claimed is: 1. A combustion chamber for a gas turbine engine, comprising: a first premixer and a second premixer oriented about an axis defined between an upstream end and a downstream end of a combustor, each premixer comprising at least one fuel injector, at least one air inlet duct, and at least one vane pack downstream of the at least one fuel injector for at least partially mixing air from the at least one air inlet duct and fuel from the at least one fuel injector; wherein each of the vane packs comprises a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air pass; wherein the at least one vane pack of the first premixer is positioned at a first axial position relative to the axis and the at least one vane pack of the second premixer is positioned at a second axial position relative to the axis, wherein the second axial position is axially staggered with respect to the first axial position. 2. The combustion chamber of claim 1, wherein the at least one vane pack comprises a plurality of vanes, wherein each vane comprises an exit location, and wherein the exit location of the at least one vane pack of the first premixer is positioned at the first axial position and the exit location of the at least one vane pack of the second premixer is positioned at the second axial position. 3. The combustion chamber of claim 1, wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially aligned with the plurality of fuel orifices of the at least one vane pack of the second premixer. 4. The combustion chamber of claim 1, wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially staggered relative to the axis and with respect to the plurality of fuel orifices of the at least one vane pack of the second premixer. 5. The combustion chamber of claim 1 wherein the first premixer and the second premixer each further comprise a diffusion tip positioned downstream of the at least one vane pack, wherein the diffusion tip of the first premixer is axially aligned with the diffusion tip of the second premixer. 6. The combustion chamber of claim 1, wherein the first premixer and the second premixer each further comprise a diffusion tip positioned downstream of the at least one vane pack, wherein the diffusion tip of the first premixer is axially staggered with respect to the diffusion tip of the second premixer. 7. The combustion chamber of claim 1, wherein the relative spacing between the first axial position and the second axial position is selected to reduce combustion dynamics produced in the combustion chamber. 8. A method for combusting fuel in a combustion chamber, comprising: mixing fuel and air in a first premixer oriented about an axis defined between an upstream end and a downstream end of a combustor, the first premixer comprising at least one fuel injector, at least one air inlet duct, and at least one vane pack downstream of the at least one fuel injector at a first axial position relative to the axis; mixing fuel and air in a second premixer comprising at least one fuel injector, at least one air inlet duct, and at least one vane pack at downstream of the at least one fuel injector at a second axial position relative to the axis, wherein the second axial position is axially staggered with respect to the first axial position; discharging the mixed fuel and air from the first premixer and the second premixer to a combustion chamber; and combusting at least a portion of the mixed fuel and air from the first premixer and the second premixer in the combustion chamber. 9. The method of claim 8, wherein the at least one vane pack comprises a plurality of vanes, each vane comprising an exit location, and wherein the exit location of the at least one vane pack of the first premixer is positioned at the first axial position and the exit location of the at least one vane pack of the second premixer is positioned at the second axial position. 10. The method of claim 8, wherein each of the plurality of vanes comprises a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air pass, and wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially aligned with the plurality of fuel orifices of the at least one vane pack of the second premixer. 11. The method of claim 8, wherein each of the plurality of vanes comprises a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air pass, and wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially staggered relative to the axis and with respect to the plurality of fuel orifices of the at least one vane pack of the second premixer. 12. The method of claim 8, wherein the first premixer and the second premixer each further comprise a diffusion tip positioned downstream of the at least one vane pack, and wherein the diffusion tip of the first premixer is axially aligned with the diffusion tip of the second premixer. 13. The method of claim 8, wherein the first premixer and the second premixer each further comprise a diffusion tip positioned at a location downstream of the at least one vane pack, and wherein the diffusion tip of the first premixer is axially staggered with respect to the diffusion tip of the second premixer. 14. The method of claim 8, wherein combusting at least a portion of the mixed fuel and air comprises facilitating a heat release oscillation that propagates upstream to the first premixer and the second premixer and produces first fuel concentration wave in the first premixer and a second fuel concentration wave in the second premixer which travel downstream to the flame burning region, the second fuel concentration wave out of phase with the first fuel concentration wave based at least in part on the relative separation of the first and second axial positions of the vane packs. 15. The method of claim 8, further comprising adjusting the axial location of at least one vane of the at least one vane pack of the first premixer or of at least one vane of the at least one vane pack of the second premixer when the type of fuel is changed from a first fuel to a second fuel. 16. A gas turbine engine, comprising: a compressor; a combustion chamber; at least a first premixer and a second premixer associated with the combustion chamber and oriented about an axis defined between an upstream end proximate the compressor and a downstream end proximate the combustion chamber, each premixer comprising at least one fuel injector, at least one air inlet duct, and at least one vane pack downstream of the at least one fuel injector for at least partially mixing air from the at least one air inlet duct and fuel from the at least one fuel injector; wherein each of the plurality of vanes comprises a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air pass; and wherein the at least one vane pack of the first premixer is positioned within the first premixer at a first axial position relative to the axis and the at least one vane pack of the second premixer is positioned within the second premixer at a second axial position relative to the axis, wherein the second axial position is axially staggered with respect to the first axial position. 17. The gas turbine engine of claim 16, wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially aligned with the plurality of fuel orifices of the at least one vane pack of the second premixer. 18. The gas turbine engine of claim 16, wherein the plurality of fuel orifices of the at least one vane pack of the first premixer are axially staggered relative to the axis and with respect to the plurality of fuel orifices of the at least one vane pack of the second premixer. 19. The gas turbine engine of claim 16, wherein the locations of the first axial position and the second axial position are selected to reduce combustion dynamics associated with the combustion chamber. 20. The gas turbine engine of claim 16, wherein the at least one vane pack comprises a first vane comprising a first plurality of fuel orifices and a second vane comprising a plurality of fuel orifices, and wherein the first plurality of fuel orifices are axially staggered relative to the axis and with respect to the second plurality of fuel orifices.