초록 ▼

A system including a multi-tube fuel nozzle, including a first plate having a first plurality of openings, a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixtur

A system including a multi-tube fuel nozzle, including a first plate having a first plurality of openings, a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, and a resilient metallic seal disposed along the first plate about the plurality of tubes.

대표청구항 ▼

1. A system, comprising: a multi-tube fuel nozzle, comprising: a first plate having a first plurality of openings spaced apart from one another;a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes comprises an air inle

1. A system, comprising: a multi-tube fuel nozzle, comprising: a first plate having a first plurality of openings spaced apart from one another;a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes comprises an air inlet, a fuel inlet, and a fuel-air mixture outlet; anda resilient metallic seal disposed along the first plate about the plurality of tubes, wherein the resilient metallic seal comprises at least one axially adjustable turn; anda housing having a wall surrounding the multi-tube fuel nozzle, wherein the resilient metallic seal is disposed between the wall and the first plate of the multi-tube fuel nozzle, and the at least one axially adjustable turn is configured to expand or contract in an axial direction in response to axial movement between the wall and the first plate of the multi-tube fuel nozzle. 2. The system of claim 1, comprising a combustor having the multi-tube fuel nozzle. 3. The system of claim 2, wherein the combustor is a gas turbine combustor. 4. The system of claim 2, comprising a gas turbine engine having the combustor with the multi-tube fuel nozzle. 5. The system of claim 1, wherein the multi-tube fuel nozzle comprises a second plate having a second plurality of openings spaced apart from one another, the plurality of tubes extends through the second plurality of openings in the second plate, the first and second plates are axially offset relative to one another by an axial offset distance, and the resilient metallic seal is configured to expand or contract in the axial direction due to axial movement between the first plate and the second plate, a first ring structure surrounding the plurality of tubes, or a combination thereof. 6. The system of claim 5, wherein the first and second plates are coupled to the plurality of tubes at the axial offset distance, and the resilient metallic seal is configured to expand or contract in the axial direction due to thermal expansion or thermal contraction of the plurality of tubes between the first and second plates. 7. The system of claim 1, wherein the at least one axially adjustable turn curves from a radially inward direction to a radially outward direction relative to an axis of the multi-tube fuel nozzle. 8. The system of claim 1, wherein the at least one axially adjustable turn comprises a plurality of alternating turns that define a wave pattern. 9. The system of claim 1, wherein the resilient metallic seal is coupled to the first plate. 10. The system of claim 9, wherein the resilient metallic seal is coupled to the wall of the housing. 11. The system of claim 1, wherein the wall of the housing comprises a first ring structure surrounding a first chamber having the plurality of tubes, wherein the first ring structure comprises a groove and a protrusion extending around the first chamber, and the resilient metallic seal is disposed in the groove between the first ring structure and the first plate. 12. The system of claim 1, wherein the wall of the housing surrounds an interior volume having the plurality of tubes, and the first plate divides the interior volume of the housing between first and second chambers having the plurality of tubes. 13. The system of claim 12, wherein the multi-tube fuel nozzle comprises a second plate having a second plurality of openings spaced apart from one another, the plurality of tubes extend through the second plurality of openings in the second plate, and the second plate divides the interior volume of the housing between the second chamber and a third chamber having the plurality of tubes. 14. The system of claim 13, wherein the multi-tube fuel nozzle comprises a third plate having a third plurality of openings spaced apart from one another, wherein the plurality of tubes extend through the third plurality of openings in the third plate, wherein the first, second, and third plates are axially offset relative to one another, wherein the third plate divides the interior volume of the housing between the third chamber and a fourth chamber having the plurality of tubes. 15. The system of claim 13, wherein the second plate comprises one or more fuel flow apertures separate from the second plurality of openings, one or more fuel flow spaces between the second plurality of openings and the plurality of tubes, or a combination thereof. 16. The system of claim 12, wherein the housing comprises a radial fuel inlet into the second chamber. 17. The system of claim 1, wherein the at least one axially adjustable turn is captured in a pocket between the wall and the first plate. 18. The system of claim 17, wherein the pocket comprises axially opposite structures and radially opposite structures relative to the axis of the multi-tube fuel nozzle. 19. A system, comprising: a multi-tube fuel nozzle, comprising: a plurality of fuel-air mixing tubes spaced apart from one another within a chamber, wherein each tube of the plurality of fuel-air mixing tubes comprises an air inlet, a fuel inlet in a sidewall of the tube, and a fuel-air mixture outlet; anda resilient metallic seal disposed along an outer perimeter about the plurality of fuel-air mixing tubes, wherein the resilient metallic seal comprises at least one axially adjustable turn that curves from a radially inward direction to a radially outward direction relative to an axis of the multi-tube fuel nozzle, and the at least one axially adjustable turn is configured to expand or contract in an axial direction in response to axial movement of the plurality of fuel-air mixing tubes. 20. The system of claim 19, wherein the at least one axially adjustable turn comprises a plurality of alternating turns that define a wave pattern. 21. The system of claim 19, wherein the at least one axially adjustable turn is configured to expand or contract in the axial direction in response to thermal expansion or thermal contraction of the plurality of fuel-air mixing tubes. 22. The system of claim 19, comprising a combustor, a gas turbine engine, or a combination thereof, having the multi-tube fuel nozzle. 23. A method, comprising: sealing a multi-tube fuel nozzle to a surrounding structure via a resilient metallic seal having at least one axially adjustable turn that curves from a radially inward direction to a radially outward direction relative to an axis of the multi-tube fuel nozzle, wherein the multi-tube fuel nozzle comprises a plurality of tubes spaced apart from one another, each tube of the plurality of tubes having an air inlet, a fuel inlet in a sidewall of the tube, and a fuel-air mixture outlet; andexpanding or contracting the at least one axially adjustable turn of the resilient metallic seal in an axial direction, while sealing, in response to thermal expansion or thermal contraction of the plurality of tubes or the surrounding structure in the axial direction. 24. The method of claim 23, wherein expanding or contracting the at least one axially adjustable turn of the resilient metallic seal comprises expanding or contracting a plurality of axially adjustable turns of the resilient metallic seal. 25. The method of claim 23, comprising capturing the at least one axially adjustable turn of the resilient metallic seal within a pocket between the plurality of tubes and the surrounding structure. 26. The method of claim 25, wherein capturing the at least one axially adjustable turn of the resilient metallic seal within the pocket comprises surrounding the at least one axially adjustable turn with axially opposite structures and radially opposite structures relative to the axis of the multi-tube fuel nozzle. 27. A system, comprising: a multi-tube fuel nozzle, comprising: a first plate having a first plurality of openings;a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes comprises an air inlet, a fuel inlet, and a fuel-air mixture outlet; anda resilient metallic seal disposed along the first plate about the plurality of tubes; anda first ring structure surrounding a first chamber having the plurality of tubes, wherein the first ring structure comprises a groove and a protrusion extending around the first chamber, and the resilient metallic seal is disposed in the groove between the first ring structure and the first plate.