Bundled tube fuel nozzle with vibration damping

1. A bundled tube fuel nozzle, comprising:

a forward plate, an intermediate plate, and an outer sleeve, wherein the forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween;

an aft plate axially spaced from the intermediate plate, wherein the intermediate plate, the aft plate, and the outer sleeve define a cooling air plenum therebetween; and

a plurality of tubes that extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate, wherein each tube of the plurality of tubes extends through a respective tube opening of a plurality of tube openings defined by the aft plate and wherein a radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening;

wherein the plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening, the at least one tube comprises a tip portion, and the tip portion of the at least one tube has an oval cross sectional shape.

2. The bundled tube fuel nozzle as in claim 1 , wherein the at least one tube is radially loaded against the inner surface at one contact point along the inner surface.

3. The bundled tube fuel nozzle as in claim 1 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface.

4. The bundled tube fuel nozzle as in claim 1 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface and divides the radial gap into two or more fluidly isolated gap segments.

5. A combustor, comprising:

an end cover coupled to an outer casing;

a bundled tube fuel nozzle disposed within the outer casing and coupled to the end cover via one or more fluid conduits, wherein the bundled tube fuel nozzle comprises:

a forward plate, an intermediate plate, and an outer sleeve, wherein the forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween;

an aft plate axially spaced from the intermediate plate, wherein the intermediate plate, the aft plate and the outer sleeve define a cooling air plenum therebetween; and

a plurality of tubes that extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate, wherein each tube of the plurality of tubes extends through a respective tube opening of a plurality of tube openings defined by the aft plate and wherein a radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening;

wherein the plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening, the at least one tube comprises a tip portion, and the tip portion of the at least one tube has an oval cross sectional shape.

6. The combustor as in claim 5 , wherein the at least one tube is radially loaded against the inner surface at one contact point along the inner surface.

7. The combustor as in claim 5 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface.

8. The combustor as in claim 5 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface and divides the radial gap into two or more fluidly isolated gap segments.

9. A gas turbine, comprising:

a compressor, a combustor downstream from the compressor and a turbine disposed downstream form the compressor, the combustor comprising an end cover coupled to an outer casing and a bundled tube fuel nozzle disposed within the outer casing and coupled to the end cover via one or more fluid conduits, wherein the bundled tube fuel nozzle comprises:

a forward plate, an intermediate plate, and an outer sleeve, wherein the forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween;

an aft plate axially spaced from the intermediate plate, wherein the intermediate plate, the aft plate and the outer sleeve define a cooling air plenum therebetween; and

a plurality of tubes that extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate, wherein each tube of the plurality of tubes extends through a respective tube opening of a plurality of tube openings defined by the aft plate and wherein a radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening;

wherein the plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening, the at least one tube comprises a tip portion, and the tip portion of the at least one tube has an oval cross sectional shape.

10. The gas turbine of claim 9 , wherein the at least one tube is radially loaded against the inner surface at one contact point along the inner surface.

11. The gas turbine of claim 9 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface.

12. The gas turbine of claim 9 , wherein the at least one tube is radially loaded against the inner surface at two or more contact points along the inner surface and divides the radial gap into two or more fluidly isolated gap segments.