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A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber t

A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber to the downstream wall portion. Each tube of the multiple tubes includes an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, and is configured to receive air and mix the air with fuel from the at least one fuel inlet. The multi-tube fuel nozzle includes a fuel conduit extending through the chamber crosswise to and around the multiple tubes. The fuel conduit includes multiple impingement cooling orifices. A fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube.

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1. A system, comprising: a multi-tube fuel nozzle having a longitudinal axis, comprising: a fuel nozzle head comprising an outer wall surrounding a chamber, wherein the outer wall comprises a downstream wall portion configured to face a combustion region;a plurality of tubes extending through the ch

1. A system, comprising: a multi-tube fuel nozzle having a longitudinal axis, comprising: a fuel nozzle head comprising an outer wall surrounding a chamber, wherein the outer wall comprises a downstream wall portion configured to face a combustion region;a plurality of tubes extending through the chamber to the downstream wall portion, wherein each tube of the plurality of tubes comprises an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, wherein each tube is configured to receive air and mix the air with fuel from the at least one fuel inlet; anda fuel conduit comprising a first baffle and a second baffle disposed within the chamber spaced apart from one another, the first and second baffles extending radially relative to the longitudinal axis, the second baffle being disposed between the first baffle and the downstream wall portion, the second baffle does not contact the outer wall, and the plurality of tubes extends through the first and second baffles, wherein the fuel conduit comprises a plurality of impingement cooling orifices disposed on the second baffle, wherein a fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube. 2. The system of claim 1, wherein the plurality of impingement cooling orifices are configured to direct fuel to impingement cool the downstream wall portion. 3. The system of claim 1, wherein each tube of the plurality of tubes extends through a first opening in the first baffle and a second opening in the second baffle, the first and second openings are oversized relative to the tube to define a first gap between the first baffle and the tube and a second gap between the second baffle and the tube, respectively, the first gap is configured to convectively cool the tube, and the second gap is configured to convectively cool the tube and the downstream wall portion. 4. The system of claim 3, wherein each first gap and second gap is configured to shrink in response to thermal expansion of the tube to increase fuel flow through the plurality of impingement cooling orifices. 5. The system of claim 1, wherein the fuel conduit comprises at least one floating baffle configured to float relative to the plurality of tubes. 6. The system of claim 5, wherein the second baffle comprises the at least one floating baffle. 7. The system of claim 1, the system comprising a turbine combustor or a gas turbine engine having the multi-tube fuel nozzle. 8. A system comprising: a turbine combustor comprising: a multi-tube fuel nozzle coupled to the turbine combustor, wherein the multi-tube fuel nozzle comprises:a fuel nozzle body comprising an outer wall surrounding a chamber;a plurality of tubes extending through the chamber, wherein each tube of the plurality of tubes comprises an air inlet, a fuel inlet, and an air-fuel mixture outlet;at least one baffle disposed with chamber, wherein the at least one baffle does not contact the outer wall and the at least one baffle comprises a plurality of impingement cooling orifices configured to direct fuel to impingement cool the multi-tube fuel nozzle, and wherein the at least one baffle extends radially relative to a longitudinal axis of the multi-tube nozzle and the plurality of tubes extends through the at least one baffle though a plurality of openings in the baffle; andwherein each tube of the plurality of tubes extends through one of the plurality of openings, each opening of the plurality of openings is oversized relative to the respective tube to define a gap, and each gap is configured to direct the fuel to convectively cool the respective tube or the outer wall. 9. The system of claim 8, wherein the plurality of impingement cooling orifices are configured to direct the fuel to impingement cool the outer wall or the plurality of tubes. 10. The system of claim 8, wherein the at least one baffle is a floating baffle configured to float relative to the plurality of tubes. 11. The system of claim 8, wherein each gap is configured to shrink in response to thermal expansion of the respective tube to increase fuel flow through the plurality of impingement cooling orifices. 12. The system of claim 8, wherein a fuel flow path extends through the impingement cooling orifices, through the chamber, and into the fuel inlet of each tube. 13. A system, comprising: a multi-tube fuel nozzle, comprising: a fuel nozzle body comprising an outer wall surrounding a chamber;a plurality of tubes extending through the chamber from a first wall portion to a second wall portion of the outer wall, wherein each tube of the plurality of tubes comprises an air inlet, a fuel inlet, and an air-fuel mixture outlet; anda fuel conduit comprising a first baffle and a second baffle disposed within the chamber spaced apart from one another, the first and second baffles extending radially relative to the longitudinal axis, the second baffle does not contact the outer wall, and the plurality of tubes extends through the first and second baffles, wherein the fuel conduit comprises a plurality of impingement cooling orifices disposed on the first or second baffle and configured to direct fuel to impingement cool the outer wall, and the fuel conduit comprises a plurality of openings disposed on both the first baffle and the second baffle and configured to direct the fuel to convectively cool the plurality of tubes and the outer wall. 14. The system of claim 13, wherein each tube of the plurality of tubes extends through a first opening in the first baffle and a second opening in the second baffle, and the first and second openings are oversized relative to the tube to define gaps between the respective first and second baffles and the tube. 15. The system of claim 14, wherein each gap is configured to shrink in response to thermal expansion of the tube to increase fuel flow through the plurality of impingement cooling orifices. 16. The system of claim 13, wherein a fuel flow path extends through the openings and the impingement cooling orifices, through the chamber, and into the fuel inlet of each tube.