Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor

1. A dual fuel nozzle for a gas turbine combustor, the dual fuel nozzle comprising:

an annular air passage;

a swirler disposed entirely in the annular air passage, the swirler imparting swirl to air flowing in the annular air passage;

a splitter ring disposed in the annular air passage, said splitter ring disposed partially downstream of the swirler for splitting the airflow from the swirler into two portions;

a hub defining a liquid fuel inlet; and

a plurality of liquid fuel jets surrounding a downstream end of the hub and in fluid communication with the liquid fuel inlet, each of the plurality of liquid fuel jets being positioned to radially eject liquid fuel into the annular air passage into contact with the splitter ring, wherein the swirler and the plurality of liquid fuel jets are positioned such that fuel/air mixing is completed in the air passage upstream of a combustion zone, and wherein the splitter ring is positioned upstream of a nozzle exit by a distance that permits the liquid fuel to vaporize before combustion.

2. A dual fuel nozzle according to claim 1 , further comprising an atomizer associated with each of the plurality of liquid fuel jets, the atomizer mixing air with the liquid fuel ejected from the plurality of fuel jets.

3. A dual fuel nozzle according to claim 2 , wherein the atomizer comprises an airblast slot disposed in alignment with each of the plurality of liquid fuel jets.

4. A dual fuel nozzle according to claim 3 , wherein the airblast slots define insulators for the liquid fuel ejected from the plurality of liquid fuel jets.

5. A dual fuel nozzle according to claim 1 , wherein the hub is removable.

6. A dual fuel nozzle according to claim 1 , wherein a trailing edge of the splitter ring is tapered.

7. A dual fuel nozzle according to claim 1 , wherein the splitter ring creates a shear layer between two concentric annular streams of swirling airflow.

8. A dual fuel nozzle according to claim 7 , wherein the splitter ring enhances shear by allowing two air streams with different swirl angles to rejoin at a trailing edge of the splitter ring.

9. A dual fuel nozzle for a gas turbine combustor, the dual fuel nozzle comprising:

a hub defining a fuel inlet;

a plurality of liquid fuel jets disposed at a downstream end of the hub and oriented to eject liquid fuel radially outward from the hub;

an annular air passage including a swirler disposed entirely within the air passage that imparts swirl to air flowing in the annular air passage; and

splitter ring disposed in the annular air passage and surrounding the plurality of liquid fuel jets, said splitter ring disposed partially downstream of the swirler for splitting the airflow from the swirler into two portions, wherein the swirler and the plurality of liquid fuel jets are positioned such that fuel/air mixing is completed in the air passage upstream of a combustion zone, and wherein the splitter ring is positioned upstream of a nozzle exit by a distance that permits the liquid fuel to vaporize before combustion.

10. A dual fuel nozzle according to claim 9 , further comprising an atomizer associated with each of the plurality of liquid fuel jets, the atomizer mixing air with the liquid fuel ejected from the plurality of fuel jets.

11. A dual fuel nozzle according to claim 10 , wherein the atomizer comprises an airblast slot disposed in alignment with each of the plurality of liquid fuel jets.

12. A dual fuel nozzle according to claim 11 , wherein the airblast slots define insulators for the liquid fuel ejected from the plurality of liquid fuel jets.

13. A dual fuel nozzle according to claim 9 , wherein a trailing edge of the splitter ring is tapered.

14. A dual fuel nozzle according to claim 9 , wherein the nozzle is operable with gas fuel.

15. A method of mixing liquid fuel and air in a dual fuel nozzle for a gas turbine combustor, the gas turbine combustor including a hub defining a fuel inlet, a plurality of liquid fuel jets disposed at a downstream end of the hub and oriented to eject liquid fuel radially outward from the hub, an annular air passage including a swirler disposed entirely within the air passage, and a splitter ring disposed in the annular air passage and surrounding the plurality of liquid fuel jets, the method comprising:

flowing air through the annular air passage and imparting swirl to the flowing air by the swirler, wherein said splitter ring is disposed partially downstream of the swirler, the splitter ring splitting the airflow from the swirler into two portions;

inputting liquid fuel through the fuel inlet;

ejecting liquid fuel radially from the liquid fuel jets into contact with the splitter ring, wherein liquid fuel impinging on the splitter ring forms a fuel film on the splitter ring that mixes with the swirling air flowing in the annular air passage;

positioning the swirler and the plurality of liquid fuel jets such that fuel/air mixing is completed in the air passage upstream of a combustion zone; and

positioning the splitter ring upstream of a nozzle exit by a distance that permits the liquid fuel to vaporize before combustion.

16. A method according to claim 15 , further comprising insulating the liquid fuel ejected from the liquid fuel jets.