Prefilming fuel/air mixer

1. A method for providing a fuel/air mixture in a turbine combustor assembly, the method comprising:

receiving fuel at a fuel injector coupled to a fuel/air mixture assembly, the fuel/air mixture assembly comprising a plurality of fuel/air mixer elements, each of the fuel/air mixer elements comprising at least one prefilmer located within an interior cavity of the respective fuel/air mixer element, where receiving fuel at the fuel injector comprises receiving the fuel at a tip portion of the fuel injector, the tip portion comprising a central fuel outlet and a plurality of peripheral fuel outlets, each of the peripheral fuel outlets being fluidically coupled to a respective fuel injection port of each prefilmer;

radially directing the fuel from the fuel injector into an axial inner air flow passage of the at least one prefilmer of each fuel/air mixture element; and

axially directing air through the axial inner air flow passage of the at least one prefilmer of each fuel/air mixture element.

2. The method of claim 1 , where at least one of the peripheral fuel outlets comprises a non-atomizing fuel injection orifice producing a plain jet of liquid fuel, and where the central fuel outlet comprises at least one of an air-blast injector tip and a pressure atomizing injector tip producing an atomized spray of fuel.

3. The method of claim 1 , where radially directing the fuel into the axial inner air flow passage of the at least one prefilmer comprises directing the fuel through a fuel injector port of the at least one prefilmer, the fuel injection port being biased in an offset direction relative to an axial centerline of the at least one prefilmer.

4. The method of claim 3 , where the offset direction is in accord with a curved inner wall of the at least one prefilmer.

5. The method of claim 4 , where the at least one prefilmer comprises an air swirler residing within the axial inner air flow passage at a location upstream of the fuel injection port, such that the axially directed air traversing the inner air flow passage is forced into a swirling motion along the inner wall to carry the fuel.

6. The method of claim 1 , further comprising:

axially directing additional air through the interior cavity of each respective fuel/air mixer element, and

shielding the radially directed fuel from the axially directed air traversing the interior cavities.

7. The method of claim 6 , where shielding the radially directed fuel comprises providing an at least partially cupped channel leading from the fuel injector to a fuel injector port of each prefilmer.

8. The method of claim 7 , where the partially cupped channel is integrated with a trailing surface of a swirling vane residing on an outer surface of each prefilmer.

9. The method of claim 1 , where the at least one prefilmer comprises a plurality of radial fuel injection ports and at least one additional axial inner air flow passage concentric with the axial inner air flow passage, each of the fuel injection ports being arranged to direct a separate fuel stream into a respective one of the axial inner air flow passage or the at least one additional axial inner air flow passage.

10. A method for providing a fuel/air mixture in a turbine combustor assembly, the method comprising:

receiving fuel at a fuel injector coupled to a fuel/air mixture assembly, the fuel/air mixture assembly comprising a plurality of fuel/air mixer elements, each of the fuel/air mixer elements comprising at least one prefilmer located within an interior cavity of the respective fuel/air mixer element;

radially directing the fuel from the fuel injector into an axial inner air flow passage of the prefilmer of each fuel/air mixture element;

axially directing air through the axial inner air flow passage of the prefilmer of each fuel/air mixture element;

axially directing additional air through the interior cavity of each respective fuel/air mixer element; and

shielding the radially directed fuel from the axially directed air traversing the interior cavities.

11. The method of claim 10 , where shielding the radially directed fuel comprises providing an at least partially cupped channel leading from the fuel injector to a fuel injector port of each prefilmer.

12. The method of claim 11 , where the partially cupped channel is integrated with a trailing surface of a swirling vane residing on an outer surface of each prefilmer.

13. The method of claim 10 , where radially directing the fuel into the axial inner air flow passage of the at least one prefilmer comprises directing the fuel through a fuel injector port of the at least one prefilmer, the fuel injection port being biased in an offset direction relative to an axial centerline of the at least one prefilmer.

14. The method of claim 13 , where the offset direction is in accord with a curved inner wall of the at least one prefilmer.

15. The method of claim 14 , where the at least one prefilmer comprises an air swirler residing within the axial inner air flow passage at a location upstream of the fuel injection port, such that the axially directed air traversing the inner air flow passage is forced into a swirling motion along the inner wall to carry the fuel.

16. The method of claim 10 , where the at least one prefilmer comprises a plurality of radial fuel injection ports and at least one additional axial inner air flow passage concentric with the axial inner air flow passage, each of the fuel injection ports being arranged to direct a separate fuel stream into a respective one of the axial inner air flow passage or the at least one additional axial inner air flow passage.