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The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the l

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.

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1. A combustor for combusting a flow of fuel and a flow of air, comprising: a plurality of fuel nozzles;a lean pre-nozzle fuel injection system positioned upstream of the plurality of fuel nozzles to premix the flow of fuel and the flow of air; anda casing positioned about a cap baffle, wherein the

1. A combustor for combusting a flow of fuel and a flow of air, comprising: a plurality of fuel nozzles;a lean pre-nozzle fuel injection system positioned upstream of the plurality of fuel nozzles to premix the flow of fuel and the flow of air; anda casing positioned about a cap baffle, wherein the casing and the cap baffle form a premixing annulus having a length defined between the lean pre-nozzle fuel injection system and a distal end of the cap baffle, wherein the lean pre-nozzle fuel injection system is disposed about an upstream end of the cap baffle, wherein the plurality of fuel nozzles are positioned downstream of the premixing annulus, wherein the lean pre-nozzle fuel injection system is positioned upstream of the premixing annulus, and wherein the distal end of the cap baffle and a corresponding portion of the casing are curved inward towards the plurality of fuel nozzles. 2. The combustor of claim 1, wherein each of the plurality of fuel nozzles comprises a fuel injector and a swirler. 3. The combustor of claim 1, wherein each of the plurality of fuel nozzles comprises a plurality of outer fuel nozzles. 4. The combustor of claim 1, wherein the plurality of fuel nozzles comprises a bellmouth. 5. The combustor of claim 1, wherein the cap baffle and the casing expand in a direction towards an end cover. 6. The combustor of claim 1, wherein the premixing annulus comprises a smooth turning portion adjacent to the plurality of fuel nozzles. 7. The combustor of claim 1, wherein the lean pre-nozzle fuel injection system comprises a plurality of fuel injectors. 8. The combustor of claim 7, wherein each of the plurality of fuel injectors comprises a streamlined wing-like shape. 9. The combustor of claim 7, wherein each of the plurality of fuel injectors comprises a plurality of injector holes. 10. The combustor of claim 4, wherein the distal end of the cap baffle extends beyond the bellmouth. 11. A combustor for combusting a flow of fuel and a flow of air, comprising: a plurality of fuel nozzles;a lean pre-nozzle fuel injection system positioned upstream of the plurality of fuel nozzles to premix the flow of fuel and the flow of air;a casing positioned about a cap baffle, wherein the casing and the cap baffle form a premixing annulus having a length defined between the lean pre-nozzle fuel injection system and a distal end of the cap baffle, wherein the lean pre-nozzle fuel injection system is disposed about an upstream end of the cap baffle, wherein the plurality of fuel nozzles are positioned downstream of the premixing annulus, wherein the lean pre-nozzle fuel injection system is positioned upstream of the premixing annulus; anda bellmouth disposed at an upstream end of the plurality of fuel nozzles, wherein the distal end of the cap baffle extends beyond the bellmouth, and wherein the distal end of the cap baffle and a corresponding portion of the casing are curved inward towards the plurality of fuel nozzles. 12. The combustor of claim 11, wherein the premixing annulus comprises a smooth turning portion adjacent to the plurality of fuel nozzles. 13. The combustor of claim 11, wherein the lean pre-nozzle fuel injection system comprises a plurality of fuel injectors. 14. The combustor of claim 11, wherein each of the plurality of fuel injectors comprises a streamlined wing-like shape.