Fuel oil axial stage combustion for improved turbine combustor performance
A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.
1. A combustion system for a turbine engine comprising:
a primary fuel injection system for injecting a fuel;
a combustion basket located downstream of the primary fuel injection system, wherein the primary fuel injection system injects the fuel into the combustion basket creating a primary combustion zone;
a transition system located downstream of the primary combustion zone, wherein a portion of the transition system surrounds the combustion basket;
a secondary fuel injection system located downstream of the primary fuel injection system, wherein the secondary fuel injection system comprises an air scoop; wherein the secondary fuel injection system injects the fuel downstream from where the primary fuel injection system injected the fuel and upstream of an exit from the transition system, wherein the injection of the fuel by the secondary fuel injection system creates a secondary combustion zone, wherein the fuel is not mixed with water, and
a shell surrounding at least a portion of the combustion basket and at least a portion of the transition system that allows air to flow through,
whereon the air scoop is located within the shell and configured to mix the fuel injected by the secondary fuel injection system with the air delivered from the shell and inject the mixture into the secondary combustion zone.
2. The combustion system of claim 1 , wherein the secondary combustion zone is located at a location where the transition system surrounds the combustion basket.
3. The combustion system of claim 1 , wherein the secondary fuel injection system injects the fuel at an angle greater than 45 degrees with respect to a primary flow direction within the combustion basket.
4. The combustion system of claim 1 , wherein the secondary fuel injection system injects the fuel at an angle less than 90 degrees with respect to a primary flow direction within the combustion basket.
5. The combustion system of claim 1 , wherein the secondary fuel injection system injects the fuel at a 90 degree angle with respect to a primary flow direction within the combustion basket.
6. The combustion system of claim 1 , wherein the secondary fuel injection system comprises a plurality of air scoops.
7. The combustion system of claim 1 , wherein the air scoop is conical shaped.
8. The combustion system of claim 1 , wherein the air scoop has one inlet and two outlets.
9. The gas turbine engine of claim 1 , wherein the secondary fuel injection system comprises a plurality of air scoops.
10. The turbine engine of claim 1 , wherein the secondary combustion zone is located at a location where the transition system surrounds the combustion basket.
11. A method for operating a turbine engine comprising:
injecting a fuel via a primary fuel injection system into a combustion basket creating a primary combustion zone, and
injecting the fuel via a secondary fuel injection system located downstream of the primary fuel injection system and upstream of an exit of a transition system thereby creating a secondary combustion zone, wherein the secondary fuel injection system comprises an air scoop; wherein the fuel is not mixed with water,
wherein a shell surrounds at least a portion of the combustion basket and at least a portion of the transition system that allows air to flow through, and
whereon the air scoop is located within the shell and configured to mix the fuel injected by the secondary fuel injection system with the air delivered from the shell and inject the mixture into the secondary combustion zone.
12. The method of claim 11 , wherein the secondary combustion zone is located where the transition system surrounds the combustion basket.
13. The method of claim 11 , wherein the secondary fuel injection system injects the fuel at an angle greater than 45 degrees with respect to a primary flow direction within the combustion basket.
14. The method of claim 11 , wherein the secondary fuel injection system injects the fuel at an angle less than 90 degrees with respect to a primary flow direction within the combustion basket.
15. The method of claim 11 , wherein the secondary fuel injection system injects the fuel at a 90 degree angle with respect to a primary flow direction within the combustion basket.
16. The method of claim 11 , wherein the secondary fuel injection system comprises a plurality of air scoops.
17. The method of claim 11 , wherein the air scoop is conical shaped.
18. The method of claim 11 , wherein the air scoop has one inlet and two outlets.
19. A turbine engine comprising:
a primary fuel injection system for injecting a fuel;
a combustion basket located downstream of the primary fuel injection system, wherein the primary fuel injection system injects the fuel into the combustion basket creating a primary combustion zone;
a transition system located downstream of the primary combustion zone, wherein a portion of the transition system surrounds the combustion basket;
a secondary fuel injection system located downstream of the primary fuel injection system, wherein the secondary fuel injection system comprises an air scoop; wherein the secondary fuel injection system injects the fuel downstream from where the primary fuel injection system injected the fuel and upstream of an exit from the transition system, wherein the injection of the fuel by the secondary fuel injection system creates a secondary combustion zone, wherein the fuel is not mixed with water, and
a shell surrounding at least a portion of the combustion basket and at least a portion of the transition system that allows air to flow through,
whereon the air scoop is located within the shell and configured to mix the fuel injected by the secondary fuel injection system with the air delivered from the shell and inject the mixture into the secondary combustion zone.