Dual fuel gas turbine engine pilot nozzles
A pilot nozzle for a dual fuel turbine engine includes an inner air circuit, a gaseous fuel circuit radially outward from the inner air circuit, a liquid fuel circuit radially outward from the inner air circuit, an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit, and a shroud radially outward from the outer air circuit. The shroud is configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits.
1. A pilot nozzle for a dual fuel turbine engine comprising:
an inner air circuit;
a gaseous fuel circuit radially outward from the inner air circuit;
a liquid fuel circuit radially outward from the inner air circuit; an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit;
a shroud radially outward from the outer air circuit configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits, wherein the shroud includes an upstream end with a first axial position proximate to an upstream wall of a pilot nozzle end, a non-converging non-diverging section defining a longitudinal axis downstream of the upstream wall of the pilot nozzle end, and a downstream end of the shroud including a diverging portion; and
an ignition device radially inward from the inner air circuit, wherein the inner air circuit includes an outlet that is axially upstream relative to an inlet of the outer air circuit, wherein the ignition device is at least partially located upstream of the inner air circuit outlet, and wherein the ignition device is located entirely upstream of each of the outlets of each of the fuel circuits;
wherein the inner air circuit includes an inner air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the inner air circuit wall to outlets on a downstream surface of the inner air circuit wall,
wherein the outer air circuit includes an outer air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the outer air circuit wall to outlets on a downstream surface of the outer air circuit wall, wherein the downstream surface of the inner air swirler wall is axially upstream relative to the upstream surface of the outer air circuit wall.
2. The pilot nozzle as recited in claim 1 , wherein the pilot re-circulation zone is radially inward from an inner diameter of the shroud.
3. The pilot nozzle as recited in claim 1 , wherein the liquid fuel circuit is radially outward from the gaseous fuel circuit.
4. The pilot nozzle as recited in claim 1 , wherein the outer air circuit is a converging, non-swirling air circuit.
5. The pilot nozzle as recited in claim 1 , wherein the inner air circuit is a swirling air circuit.
6. The pilot nozzle as recited in claim 1 , wherein the shroud, the inner and outer air circuits and the liquid and gaseous fuel circuits are co-axial with one another.
7. The pilot nozzle as recited in claim 1 , further comprising a floating seal positioned between the ignition device and the inner air circuit.
8. The pilot nozzle as recited in claim 1 , wherein each of the inner air circuits, the gaseous fuel circuit, the liquid fuel circuit include an independent outlet into the pilot re-circulation zone, and wherein the outlets of each of the fuel circuits are downstream of at least a portion of the shroud.
9. The pilot nozzle as recited in claim 1 , wherein only the downstream end of the shroud diverges.
10. The pilot nozzle as recited in claim 1 , wherein only the downstream end of the shroud diverges.
11. A pilot nozzle for a dual fuel turbine engine comprising:
an inner air circuit;
a gaseous fuel circuit radially outward from the inner air circuit;
a liquid fuel circuit radially outward from the inner air circuit;
an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit; and,
an ignition device radially inward from the inner air circuit, wherein the inner air circuit includes an outlet that is axially upstream relative to an inlet of the outer air circuit, wherein the ignition device is at least partially located upstream of the inner air circuit outlet, and wherein the ignition device is located entirely upstream of each of the outlets of each of the fuel circuits;
wherein the inner air circuit includes an inner air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the inner air circuit wall to outlets on a downstream surface of the inner air circuit wall, wherein the outer air circuit includes an outer air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the outer air circuit wall to outlets on a downstream surface of the outer air circuit wall, wherein the downstream surface of the inner air circuit wall is axially upstream relative to the upstream surface of the outer air circuit wall.
12. A combustor system comprising:
a main nozzle;
a pilot nozzle for a dual fuel turbine engine mounted to the main nozzle, wherein the pilot nozzle comprises:
an inner air circuit;
a gaseous fuel circuit radially outward from the inner air circuit;
a liquid fuel circuit radially outward from the inner air circuit; an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit;
an ignition device radially inward from the inner air circuit, wherein the inner air circuit includes an outlet that is axially upstream relative to an inlet of the outer air circuit, wherein the ignition device is at least partially located upstream of the inner air circuit outlet, and wherein the ignition device is located entirely upstream of each of the outlets of each of the fuel circuits;
a shroud radially outward from the outer air circuit configured to stabilize a pilot re-circulation zone downstream from the inner and outer air circuits and the liquid and gaseous fuel circuits, wherein the shroud includes an upstream end with a first axial position proximate to an upstream wall of a main nozzle end, a non-converging non-diverging section defining a longitudinal axis downstream of the upstream wall of the main nozzle end, and a downstream end of the shroud including a diverging portion, wherein the inner air circuit includes an inner air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the inner air circuit wall to outlets on a downstream surface of the inner air circuit wall, wherein the outer air circuit includes an outer air circuit wall with discrete jet bores defined therethrough from inlets on an upstream surface of the outer air circuit wall to outlets on a downstream surface of the outer air circuit wall, wherein the downstream surface of the inner air circuit wall is axially upstream relative to the upstream surface of the outer air circuit wall;
a main nozzle air circuit positioned radially outward from the shroud of the pilot nozzle; and
a main nozzle fuel injector positioned radially outward from the shroud of the pilot nozzle downstream from the main nozzle air circuit, wherein the shroud is configured to re-direct air flow exiting from the main nozzle air circuit.
13. The combustor system as recited in claim 12 , wherein the main nozzle air circuit includes a plurality of air slots configured to provide cooling air to the shroud of the pilot nozzle and to provide mixing air to the main nozzle fuel injector.
14. The combustor system as recited in claim 12 , wherein the pilot re-circulation zone is radially inward from an inner diameter of the shroud.
15. The combustor system as recited in claim 12 , wherein the main nozzle fuel injector is a dual fuel injector that includes a gaseous fuel circuit and a liquid fuel circuit.
16. A pilot nozzle for a dual fuel turbine engine comprising:
an inner air circuit;
a gaseous fuel circuit radially outward from the inner air circuit;
a liquid fuel circuit radially outward from the inner air circuit;
an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit;
a shroud radially outward from the outer air circuit configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits, wherein the shroud includes an upstream end with a first axial position proximate to an upstream wall of a pilot nozzle end, a non-converging non-diverging section defining a longitudinal axis downstream of the upstream wall of the pilot nozzle end, and a downstream end of the shroud including a diverging portion; and
an ignition device radially inward from the inner air circuit, wherein the inner air circuit includes an outlet that is axially upstream relative to an inlet of the outer air circuit, wherein the ignition device is at least partially located upstream of the inner air circuit outlet, and wherein the ignition device is located entirely upstream of each of the outlets of each of the fuel circuits.