Combustor with axially staged fuel injection
A combustor with axially staged fuel injection includes an endcover and a fuel injector that extends axially downstream from the endcover. The fuel injector includes a cylindrical shell formed by an outer wall and an inner wall. A first plurality of outlets is circumferentially spaced across the inner wall. A first plurality of premix channels is defined between the outer wall and the inner wall. Each premix channel of the first plurality of premix channels is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the first plurality of outlets.
1. A combustor, comprising:
an endcover; and
a fuel injector extending axially downstream from the endcover, the fuel injector including an annular shell formed by an outer wall and an inner wall, a first plurality of outlets circumferentially spaced across the inner wall, and a first plurality of premix channels defined between the outer wall and the inner wall, wherein each premix channel of the first plurality of premix channels is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the first plurality of outlets.
2. The combustor as in claim 1 , wherein the inner wall and the outer wall of the fuel injector connect at a downstream end of the fuel injector; and wherein a cooling air cavity is defined between the inner wall and the outer wall at the downstream end.
3. The combustor as in claim 2 , wherein the fuel injector includes at least one aperture in fluid communication with the cooling air cavity and defined proximate to the downstream end of the fuel injector.
4. The combustor as in claim 1 , further comprising a fuel nozzle extending downstream from the endcover and disposed upstream from the first plurality of outlets.
5. The combustor as in claim 4 , wherein the inner wall of the fuel injector circumferentially surrounds at least a portion of the fuel nozzle.
6. The combustor as in claim 1 , wherein the inner wall of the fuel injector defines a combustion chamber upstream from the first plurality of outlets.
7. The combustor as in claim 6 , wherein the first plurality of outlets defines an annular injection plane downstream from the combustion chamber.
8. The combustor as in claim 1 , wherein a first outlet of the first plurality of outlets is axially offset from a second outlet of the first plurality of outlets.
9. The combustor as in claim 1 , wherein the fuel injector further comprises a second plurality of outlets circumferentially spaced across the outer wall and a second plurality of premix channels defined between the outer wall and the inner wall; and wherein each premix channel of the second plurality of premix channels is in fluid communication with the fuel supply, the compressed air supply and a respective outlet of the second plurality of outlets.
10. The combustor as in claim 8 , wherein a first outlet of the second plurality of outlets is axially offset from a second outlet of the second plurality of outlets.
11. A combustor, comprising:
an endcover;
a fuel nozzle extending downstream from the endcover; and
a fuel injector extending axially downstream from the endcover, the fuel injector including an annular shell formed by an outer wall and an inner wall, a first plurality of outlets circumferentially spaced across the inner wall, and a first plurality of premix channels defined between the outer wall and the inner wall, wherein the inner wall defines a primary combustion chamber downstream from the fuel nozzle, and wherein each premix channel of the first plurality of premix channels is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the first plurality of outlets.
12. The combustor as in claim 11 , wherein the inner wall and the outer wall of the fuel injector connect at a downstream end of the fuel injector, wherein a cooling air cavity is defined between the inner wall and the outer wall at the downstream end.
13. The combustor as in claim 12 , wherein the fuel injector includes at least one aperture in fluid communication with the cooling air cavity and defined proximate to the downstream end of the fuel injector.
14. The combustor as in claim 11 , wherein the inner wall of the fuel injector circumferentially surrounds at least a portion of the fuel nozzle.
15. The combustor as in claim 11 , wherein the primary combustion chamber is defined upstream from the first plurality of outlets.
16. The combustor as in claim 15 , wherein the first plurality of outlets defines an annular injection plane downstream from the primary combustion chamber.
17. The combustor as in claim 11 , wherein a first outlet of the first plurality of outlets is axially offset from a second outlet of the first plurality of outlets.
18. The combustor as in claim 11 , wherein the fuel injector further comprises a second plurality of outlets circumferentially spaced across the outer wall and a second plurality of premix channels defined between the outer wall and the inner wall, wherein each premix channel of the second plurality of premix channels is in fluid communication with the fuel supply, the compressed air supply and a respective outlet of the second plurality of outlets.
19. The combustor as in claim 18 , wherein a first outlet of the second plurality of outlets is axially offset from a second outlet of the second plurality of outlets.
20. The combustor as in claim 11 , further comprising a plurality of secondary fuel nozzles extending downstream from the endcover and annularly arranged around the fuel injector outer wall.