Combustor having mixing tube bundle with baffle arrangement for directing fuel

1. A combustor, comprising:

a. a tube bundle that extends radially across at least a portion of the combustor, wherein the tube bundle comprises an upstream surface defined by a forward plate axially separated from a downstream surface defined by an aft plate;

b. a plurality of tubes that extend from the upstream surface through the downstream surface, wherein each tube provides fluid communication through the tube bundle;

c. a barrier that extends radially inside the tube bundle between the upstream and downstream surfaces;

d. a cylinder that extends axially from the forward plate to the barrier inside the tube bundle, wherein the cylinder, the barrier and the forward plate at least partially define a fuel plenum within the tube bundle, wherein the cylinder defines a plurality of perforations circumferentially spaced about the cylinder, wherein the plurality of perforations provide for fluid communication through the cylinder into the fuel plenum; and

e. an inner conduit extending axially within the cylinder, wherein the inner conduit extends through the barrier plate and the aft plate, wherein the inner conduit and the cylinder define an annulus therebetween and wherein the perforations provide for fluid communication between the annulus and the fuel plenum.

2. The combustor as in claim 1 , wherein the cylinder is connected to the barrier.

3. The combustor as in claim 1 , wherein the cylinder is connected to the forward plate.

4. The combustor as in claim 1 , wherein the cylinder extends substantially parallel to the plurality of tubes.

5. The combustor as in claim 1 , wherein the perforations of the plurality of perforations are axially spaced along the cylinder.

6. A combustor, comprising:

a. a tube bundle that extends radially across at least a portion of the combustor, wherein the tube bundle comprises an upstream surface defined by a first plate;

b. a shroud that circumferentially surrounds the first plate to at least partially define a fuel plenum inside the tube bundle;

c. a plurality of tubes that extend through the upstream surface of the tube bundle, wherein each tube provides fluid communication through the tube bundle;

d. a second plate that extends radially inside the shroud downstream from the-upstream surface;

e. a cylinder that extends axially between the first plate and the second plate inside the tube bundle, wherein me first plate, the second plate, the shroud and the cylinder at least partially define the fuel plenum within the tube bundle, wherein the cylinder defines a plurality of perforations provide for fluid communication through the cylinder into the fuel plenum; and

f. an inner conduit extending axially within the cylinder, wherein the inner conduit and the cylinder define an annulus therebetween and wherein the perforations provide for fluid communication between the annulus and the fuel plenum.

7. The combustor as in claim 6 , wherein the cylinder is connected to the second plate.

8. The combustor as in claim 6 , wherein the cylinder is connected to the upstream surface.

9. The combustor as in claim 6 , wherein the cylinder extends substantially parallel to the plurality of tubes.

10. The combustor as in claim 6 , wherein the combustor is incorporated into a turbomachine.

11. A gas turbine, comprising:

a. a compressor;

b. a combustor downstream from the compressor;

c. a turbine downstream from the combustor;

d. a tube bundle that extends radially across at least a portion of the combustor, wherein the tube bundle comprises an upstream surface defined by a forward plate axially separated from a downstream surface defined by an aft plate;

e. a shroud that circumferentially surrounds the upstream and downstream surfaces to at least partially define a fuel plenum inside the tube bundle;

f. a plurality of tubes that extend from the upstream surface through the fuel plenum and the downstream surface of the tube bundle, wherein each tube provides fluid communication through the tube bundle;

g. a barrier that extends radially inside the fuel plenum between the upstream, and downstream surfaces; and

h. a cylinder that extends axially from the forward plate to the barrier inside the tube bundle, wherein the cylinder, the barrier and the forward plate at least partially define the fuel plenum within the tube bundle, wherein the cylinder defines a plurality of perforations circumferentially spaced about the cylinder, wherein the plurality of perforations provide for fluid communication through the cylinder into the fuel plenum; and

i. an inner conduit extending axially within the cylinder, wherein the inner conduit extends through the barrier plate and the aft plate, wherein the inner conduit and the cylinder define an annulus therebetween and wherein the perforations provide for fluid communication between the annulus and the fuel plenum.

12. The gas turbine as in claim 11 , wherein the cylinder is connected to the barrier.

13. The combustor as in claim 11 , wherein the cylinder is connected to the upstream surface.

14. The combustor as in claim 11 , wherein the perforations of the plurality of perforations are axially spaced along the cylinder.