Micromixer for use with liquid fuel
A micromixer of a gas turbine has a plurality of tubes each having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor. At least some of the tubes have a liquid fuel injector, and the liquid fuel injector projects into one of the tubes. The liquid fuel injector has a ramped upstream surface and two converging side surfaces. The ramped upstream surface compresses the flow passing thereover, and a top surface of the liquid fuel injector comprises a liquid fuel outlet.
1. A micromixer of a gas turbine, the micromixer comprising:
a plurality of tubes each having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor;
wherein the combustor comprises a plurality of fuel nozzles positioned at a head end, at least one of the plurality of fuel nozzles includes the micromixer, and
at least some of the plurality of tubes having a liquid fuel injector, the liquid fuel injector projecting into at least one of the plurality of tubes, the liquid fuel injector having a ramped upstream surface and two converging side surfaces, the ramped upstream surface compressing the flow passing thereover, and a top surface of the liquid fuel injector comprises a liquid fuel outlet.
2. The micromixer of claim 1 , the plurality of tubes having a nozzle section located between an upstream portion of the plurality of tubes and a downstream portion of the plurality of tubes, the upstream portion of the plurality of tubes has a larger internal diameter than the downstream portion of the plurality of tubes, and wherein the liquid fuel injector is located at least partially in the nozzle section.
3. The micromixer of claim 2 , wherein the ramped upstream surface is located in both the upstream portion and the nozzle section.
4. The micromixer of claim 1 , the liquid fuel injector having a fuel conduit surrounded at least partially by a cooling conduit, the liquid fuel outlet is an outlet of the fuel conduit.
5. The micromixer of claim 4 , wherein the fuel conduit projects substantially radially inward into one of the tubes.
6. The micromixer of claim 4 , wherein the cooling conduit has a cooling outlet located in the top surface, and the cooling outlet is formed in an arcuate shape, and wherein the cooling outlet is located substantially downstream of the liquid fuel outlet.
7. The micromixer of claim 6 , wherein the cooling conduit comprises a plurality of cooling outlets located on the two converging side surfaces.
8. The micromixer of claim 7 , wherein the plurality of cooling outlets of the two converging side surfaces are configured to extend axially along at least one of the plurality of tubes, and are substantially perpendicular to a radial direction with respect to the plurality of tubes.
9. The micromixer of claim 1 , wherein the ramped upstream surface forms an angle of 120 degrees to 150 degrees from an inner wall of an upstream portion of the plurality of tubes.
10. The micromixer of claim 1 , further comprising a plurality of turbulators located upstream of the liquid fuel outlet, each of the plurality of turbulators having a ramped upstream surface and two converging side surfaces.
11. The micromixer of claim 10 , further comprising a cavity that surrounds at least a portion of the liquid fuel outlet, the cavity supplying a cooling air flow that cools fuel in the liquid fuel outlet and enhances fuel and/or air mixing while reducing fuel entrainment on an interior surface of the plurality of tubes.
12. A gas turbine having a micromixer, the micromixer comprising:
a plurality of tubes each having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor;
wherein the combustor comprises a plurality of fuel nozzles positioned at a head end, at least one of the plurality of fuel nozzles include the micromixer, and
at least some of the plurality of tubes having a liquid fuel injector, the liquid fuel injector projecting into at least one of the plurality of tubes, the liquid fuel injector having a ramped upstream surface and two converging side surfaces, the ramped upstream surface compressing the flow passing thereover, and a top surface of the liquid fuel injector comprises a liquid fuel outlet.
13. The gas turbine of claim 12 , the plurality of tubes having a nozzle section located between an upstream portion of the plurality of tubes and a downstream portion of the plurality of tubes, the upstream portion of the plurality of tubes has a larger internal diameter than the downstream portion of the plurality of tubes, and wherein the liquid fuel injector is located at least partially in the nozzle section.
14. The gas turbine of claim 13 , wherein the ramped upstream surface is located in both the upstream portion and the nozzle section.
15. The gas turbine of claim 12 , the liquid fuel injector having a fuel conduit surrounded at least partially by a cooling conduit, the liquid fuel outlet is an outlet of the fuel conduit.
16. The gas turbine of claim 15 , wherein the fuel conduit projects substantially radially inward into at lea one of the plurality of tubes.
17. The gas turbine of claim 15 , wherein the cooling conduit has a cooling outlet located in the top surface.
18. The gas turbine of claim 17 , wherein the cooling outlet in the top surface is formed in an arcuate shape, and wherein the cooling outlet is located substantially downstream of the liquid fuel outlet.
19. The gas turbine of claim 12 , further comprising a plurality of turbulators located upstream of the liquid fuel outlet, each of the plurality of turbulators having a ramped upstream surface and two converging side surfaces.
20. The gas turbine of claim 19 , further comprising a cavity that surrounds at least a portion of the liquid fuel outlet, the cavity supplying a cooling air flow that cools fuel in the liquid fuel outlet and enhances fuel and/or air mixing while reducing fuel entrainment on an interior surface of the plurality of tubes.