Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.
1. An injector for a combustor of a gas turbine engine comprising:
a swirler of a radial fuel injection system positioned downstream of an axial pilot fuel injection system;
a fuel nozzle located within the swirler, the fuel nozzle comprising a multiple of fuel injector orifices operable to provide a biased radial fuel distribution to fuel enrich a radial location with respect to an exit diameter of the swirler, wherein the multiple of fuel injector orifices comprises a first set of fuel injector orifices and a second set of fuel injector orifices in the fuel nozzle, the second set of fuel injector orifices downstream of the first set of fuel injector orifices with respect to the swirler;
a first fuel manifold in communication with the first set of fuel injector orifices and a second fuel manifold in communication with the second set of fuel injector orifices; and
a fuel divider valve that selectively communicates a respective percentage of fuel flow to the first set of fuel injector orifices and the second set of fuel injector orifices to provide a selective flow split between the first set of fuel injector orifices and the second set of fuel injector orifices.
2. The injector as recited in claim 1 , wherein the biased radial fuel distribution within the swirler provides a fuel enriched bias to fuel enrich an outer portion of the jet with respect to an exit diameter of the swirler.
3. The injector as recited in claim 1 , wherein the biased radial fuel distribution within the swirler provides a fuel enriched bias to fuel enrich a jet leading edge with respect to a cross-flow of hot combustion products from an upstream pilot zone.
4. The injector as recited in claim 1 , wherein the biased radial fuel distribution within the swirler provides a fuel enriched bias to fuel enrich a wake with respect to a cross-flow of hot combustion products from an upstream pilot zone.
5. The injector as recited in claim 1 , wherein the biased radial fuel distribution within the swirler provides a fuel enriched bias with respect to a flameholder.
6. The injector as recited in claim 1 , wherein the fuel divider valve is mechanical.
7. The injector as recited in claim 1 , wherein the fuel divider valve is electrical.
8. The injector as recited in claim 1 , wherein the fuel injector orifices are located downstream of the swirler with respect to a combustion chamber.
9. The injector as recited in claim 1 , further comprising a V-gutter at the exit of the injector.
10. The injector as recited in claim 1 , wherein the biased radial fuel distribution provides a fuel jet penetration at 55% of combustor radius.
11. The injector as recited in claim 1 , wherein the biased radial fuel distribution provides a fuel jet penetration of a first set of fuel injector orifices of 27.5% of combustor radius and 82.5% of combustor radius for a second set of fuel injector orifices which results in a shifted radial Fuel/Air distribution.
12. An injector for a combustor of a gas turbine engine comprising:
a swirler of a radial fuel injection system positioned downstream of an axial pilot fuel injection system; and
a fuel nozzle located within the swirler, the fuel nozzle comprising a first set of fuel injector orifices and a second set of fuel injector orifices, the second set of fuel injector orifices downstream of the first set of fuel injector orifices with respect to the swirler, at least one of the sets of fuel injector orifices arranged to tailor the radial fuel air distribution profile, wherein the multiple of fuel injector orifices comprises a first set of fuel injector orifices and a second set of fuel injector orifices in the fuel nozzle, the second set of fuel injector orifices downstream of the first set of fuel injector orifices with respect to the swirler;
a first fuel manifold in communication with the first set of fuel injector orifices and a second fuel manifold in communication with the second set of fuel injector orifices; and
a fuel divider valve that selectively communicates a respective percentage of fuel flow to the first set of fuel injector orifices and the second set of fuel injector orifices to provide a selective flow split between the first set of fuel injector orifices and the second set of fuel injector orifices.
13. The injector as recited in claim 12 , wherein at least one of the sets of fuel injector orifices is arranged to provide a fuel enriched bias to fuel enrich a radial location with respect to an exit diameter of the swirler.
14. The injector as recited in claim 12 , wherein at least one of the sets of fuel injector orifices is arranged to provide a fuel enriched bias to fuel enrich an outer portion of the jet with respect to an exit diameter of the swirler.
15. The injector as recited in claim 12 , wherein at least one of the sets of fuel injector orifices is arranged to provide a fuel enriched bias to fuel enrich a jet leading edge from the swirler with respect to a cross-flow of hot combustion products from an upstream pilot zone.
16. The injector as recited in claim 12 , wherein at least one of the sets of fuel injector orifices is arranged to provide a fuel enriched bias with respect to fuel enrich a wake from the swirler with respect to a cross-flow of hot combustion products from an upstream pilot zone.
17. The injector as recited in claim 12 , wherein at least one of the sets of fuel injector orifices is arranged to provide a fuel enriched bias with respect to a flameholder.
18. The injector as recited in claim 12 , further comprising a first fuel manifold in communication with the first set of fuel injector orifices and a second fuel manifold in communication with the second set of fuel injector orifices.
19. The injector as recited in claim 18 , further comprising a fuel divider valve that selectively communicates a respective percentage of fuel flow to the first set of fuel injector orifices and the second set of fuel injector orifices to provide a selective flow split between the first set of fuel injector orifices and the second set of fuel injector orifices.
20. The injector as recited in claim 19 , wherein the fuel divider valve is at least one of a mechanical or electrical divider valve.
21. A method for injecting fuel into a combustor of a gas turbine engine, comprising:
tailoring a radial fuel air distribution profile within a swirler of a radial fuel injection system positioned downstream of an axial pilot fuel injection system with an injector comprising a first set of fuel injector orifices and a second set of fuel injector orifices, the second set of fuel injector orifices downstream of the first set of fuel injector orifices with respect to the swirler, and
selectively communicating a respective percentage of fuel flow through a fuel divider valve to the first set of fuel injector orifices and the second set of fuel injector orifices to provide a selective flow split between the first set of fuel injector orifices and the second set of fuel injector orifices.
22. The method as recited in claim 21 , wherein tailoring the radial fuel air distribution profile comprises fuel shifting between the first set of fuel injector orifices and the second set of fuel injector orifices.
23. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting the fuel split to 50/50.
24. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting fuel split to 75/25.
25. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting the fuel to anchor the flame.
26. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting the fuel to move the fuel jet radially outward.
27. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting the fuel to 55% of combustor radius.
28. The method as recited in claim 22 , wherein tailoring the radial fuel air distribution profile comprises shifting the fuel to provide a fuel jet penetration of the first set of fuel injector orifices of 27.5% of combustor radius and 82.5% of combustor radius for the second set of fuel injector orifices.