Dual fuel gas turbine engine pilot nozzles
AssigneeDelavan Inc.
InventorsLev Alexander Prociw, Jason A. Ryon, Jacob Greenfield
Life of this patent
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Abstract
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.
Claims18
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
- 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.
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.
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;
- and
- 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;
- 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.
Dependencies are inferred from the claim text.