Circumferential 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 circumferential 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 circumferential 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; and
a fuel nozzle located within the swirler, the fuel nozzle comprising a multiple of fuel injector orifices operable to provide a biased circumferential fuel distribution to fuel enrich a circumferential location with respect to an exit diameter of the swirler, the fuel injector orifices located downstream of the swirler with respect to a combustion chamber, 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.
2. The injector as recited in claim 1 , wherein the biased circumferential 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 circumferential 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 circumferential fuel distribution within the swirler provides a fuel enriched bias with respect 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 circumferential fuel distribution within the swirler provides a fuel enriched bias with respect to a flameholder.
6. The injector as recited in claim 1 , 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.
7. The injector as recited in claim 6 , 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.
8. The injector as recited in claim 7 , wherein the fuel divider valve is mechanical.
9. The injector as recited in claim 7 , wherein the fuel divider valve is electrical.
10. The injector as recited in claim 1 , wherein the axial pilot fuel injection system provides 10%-35% of a combustor airflow and the radial main fuel injection system provides 30%-60% of combustor airflow.
11. The injector as recited in claim 10 , wherein a multiple of dilution holes provide about 5%-20% of the combustor airflow.
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 includes 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 circumferential fuel air distribution profile within the swirler.
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 circumferential 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. 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 multiple of fuel injector orifices operable to provide a biased circumferential fuel distribution to fuel enrich a circumferential location with respect to an exit diameter of the swirler, the fuel injector orifices located downstream of the swirler with respect to a combustion chamber,
wherein the axial pilot fuel injection system comprises a multiple of forward fuel nozzles circumferentially spaced apart between about 80%-200% of a bulkhead height;
wherein the radial fuel injection system comprises a multiple of outer fuel nozzles and inner fuel nozzles axially spaced a distance D between 50%-150% of the bulkhead height.
22. 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 multiple of fuel injector orifices operable to provide a biased circumferential fuel distribution to fuel enrich a circumferential location with respect to an exit diameter of the swirler, the fuel injector orifices located downstream of the swirler with respect to a combustion chamber, wherein the radial fuel injection system comprises a multiple of outer fuel nozzles and inner fuel nozzles axially spaced a distance D between 50%-150% of a bulkhead height.
23. The injector as recited in claim 22 , wherein the axial pilot fuel injection system comprises a multiple of forward fuel nozzles circumferentially spaced apart between about 80%-200% of a bulkhead height.