Combustor burner vanelets
The present application provides a burner for use with a combustor of a gas turbine engine. The burner may include a center hub, a shroud, a pair of fuel vanes extending from the center hub to the shroud, and a vanelet extending from the center hub and/or the shroud and positioned between the pair of fuel vanes.
1. A burner for use with a combustor of a gas turbine engine, comprising:
a center hub;
a shroud;
a pair of fuel vanes extending from the center hub to the shroud; and
a vanelet extending from the center hub and/or the shroud and positioned between the pair of fuel vanes.
2. The burner of claim 1 , further comprising a plurality of fuel vanes and a plurality of vanelets with one of the plurality of vanelets positioned between each pair of the plurality of fuel vanes.
3. The burner of claim 1 , wherein the vanelet comprises a fuel injection port.
4. The burner of claim 2 , wherein one or more of the plurality of vanelets comprise a fuel injection port.
5. The burner of claim 1 , wherein each of the pair of fuel vanes comprises an airfoil shape.
6. The burner of claim 1 , wherein each of the pair of fuel vanes comprises an upstream end and a downstream end and wherein the vanelet is positioned about the downstream end.
7. The burner of claim 1 , wherein each of the pair of fuel vanes comprises an upstream end and a downstream end and wherein the vanelet is positioned at least in part beyond the downstream end.
8. The burner of claim 1 , wherein the vanelet comprises a quenching surface.
9. The burner of claim 1 , wherein the vanelet comprises a sequestering surface.
10. A method of mixing fuel and air in a combustor burner of a gas turbine, comprising:
flowing the air into a swozzle assembly;
flowing the fuel through a plurality of fuel vanes in the swozzle assembly;
imparting swirl to the flow of air and the flow of fuel to create a premixed flow; and
positioning a vanelet between a pair of the plurality of fuel vanes so as to at least maintain the premixed flow at a predetermined velocity as the premixed flow leaves the plurality of fuel nozzles.
11. The method of claim 10 , wherein flowing the fuel comprises flowing a syngas.
12. The method of claim 10 , wherein flowing the fuel comprises flowing natural gas.
13. The method of claim 10 , further comprising flowing a secondary flow of fuel through the vanelet.
14. The method of claim 13 , wherein flowing a secondary flow of fuel comprises flowing a diluent or an inert gas.
15. The method of claim 10 , wherein positioning a vanelet between a pair of the plurality of fuel vanes comprises positioning a plurality of vanelets.
16. A swozzle assembly for use with a combustor of a gas turbine engine, comprising:
a center hub;
a shroud;
a plurality of swozzle vanes extending from the center hub to the shroud; and
a plurality of vanelets extending from the center hub and/or the shroud and with one of the plurality of vanelets positioned between each pair of the plurality of swozzle vanes.
17. The swozzle assembly of claim 16 , wherein one or more of the plurality of vanelets comprise a fuel injection port.
18. The swozzle assembly of claim 16 , wherein the plurality of swozzle vanes comprises an upstream end and a downstream end and wherein the plurality of vanelets is positioned about the downstream end.
19. The swozzle assembly of claim 16 , wherein the plurality of swozzle vanes comprises an upstream end and a downstream end and wherein the plurality of vanelets is positioned at least in part beyond the downstream end.
20. The swozzle assembly of claim 16 , wherein the plurality of vanelets comprises a quenching surface.