초록 ▼

A gas turbine engine fuel injector is disclosed having a plurality of fuel injection circuits that are structured to deliver fuel to air passageways. In one non-limiting embodiment, one of the fuel injection circuits includes a plain jet airblast injector that delivers fuel to an air passageway. In

A gas turbine engine fuel injector is disclosed having a plurality of fuel injection circuits that are structured to deliver fuel to air passageways. In one non-limiting embodiment, one of the fuel injection circuits includes a plain jet airblast injector that delivers fuel to an air passageway. In some applications the plain jet can extend across the air passageway and deliver a fuel to an opposite surface to form a fuel film. The fuel film can then be sheared between an air in the air passageway and an air in a nearby air passageway. Another of the fuel injection circuits includes a fuel filmer structured to deliver fuel to an air passageway that can then be sheared by an air in the air passageway and an air in the air passageway that included the plain jet airblast injector.

대표청구항 ▼

1. An apparatus comprising: a gas turbine engine having a fuel injector including a first fuel circuit for delivering fuel to a first air passage anda second fuel circuit for delivering fuel to a second air passage, the first air passage adjacent to the second air passage,the first fuel circuit stru

1. An apparatus comprising: a gas turbine engine having a fuel injector including a first fuel circuit for delivering fuel to a first air passage anda second fuel circuit for delivering fuel to a second air passage, the first air passage adjacent to the second air passage,the first fuel circuit structured to deliver fuel transverse to an airflow passing through the first air passage andthe second fuel circuit including a fuel filmer structured to deliver fuel to a shear region of the fuel injector defined by the airflow from the first air passage and an airflow from the second air passage,wherein the second fuel circuit includes an opening in a radially outer wall of the second air passage that is structured to deliver fuel to a filming surface of the second air passage, the second fuel circuit including a fuel swirler upstream of the opening,wherein the first air passage is located radially outward of the second air passage, andwherein the first fuel circuit includes a plain jet injector, and the fuel injector is operable to produce a film of fuel on a surface of the first air passage opposite the plain jet injector. 2. The apparatus of claim 1, wherein a side of the first air passage that includes a discharge opening of the plain jet injector extends to the shear region of the fuel injector, the shear region defined by a convergence of the first air passage and the second air passage. 3. The apparatus of claim 2, wherein the first air passage includes a first air swirler and the second air passage includes a second air swirler. 4. The apparatus of claim 3, which further includes a third air passage having a third air swirler located radially outward of the second air swirler, the third air passage merging with the first air passage downstream of the plain jet injector. 5. The apparatus of claim 2, wherein the first fuel circuit is a main fuel circuit and the second fuel circuit is a pilot circuit. 6. The apparatus of claim 5, wherein the surface of the first air passage terminating at a convergence of the first air passage and a third air passage having a third air swirler. 7. The apparatus of claim 1, wherein the plain jet injector is structured to deliver fuel in a direction away from the second fuel circuit and toward a third air passage that includes a third air swirler. 8. An apparatus comprising: a gas turbine engine fuel injector including a plain jet injector structured to deliver fuel transverse to a first air passage, the plain jet injector structured to produce a film of fuel on a surface of the first air passage opposite the plain jet injector,a fuel filmer disposed in a second air passage, the fuel filmer structured to deliver fuel to a filming surface of the second air passage through an opening, the filming surface and the opening located in a radially outer wall of the second air passage, andan air swirler located upstream in the second air passage,the first air passage adjacent the second air passage, the first air passage and the second air passage structured to converge from a radially outer location inward toward a confluence region; wherein the first air passage is located radially outward of the second air passage; andwherein the fuel filmer is structured to further deliver the fuel from the filming surface to the confluence region of the first air passage and the second air passage. 9. The apparatus of claim 8, wherein the air swirler located upstream in the second air passage is a first swirler structured to impart a swirl to an airstream traversing the second air passage, the apparatus further comprising a second swirler structured to impart a swirl to an airstream traversing the first air passage. 10. The apparatus of claim 9, wherein the plain jet injector is positioned downstream of the first swirler. 11. The apparatus of claim 8, wherein the plain jet injector is operable to deliver a liquid fuel to the surface of the first air passage opposite the plain jet injector to form the film of fuel on the surface of the first air passage. 12. The apparatus of claim 11, which further includes a third air passage having a third air swirler, the liquid fuel conveyed to a convergence of the first air passage and the third air passage. 13. The apparatus of claim 12, wherein the gas turbine engine fuel injector is coupled with a gas turbine engine and is structured to deliver fuel to a combustor of the gas turbine engine. 14. The apparatus of claim 12, which further includes a main fuel circuit having the plain jet injector and a pilot fuel circuit having the fuel filmer. 15. An apparatus comprising: a gas turbine engine having a combustor anda fuel injector structured to deliver fuel to the combustor,the fuel injector having: a first fuel opening operable to deliver fuel to a first air passage, the first fuel opening opposite a filming surface of the first air passage; anda second fuel opening operable to deliver fuel to a filming surface of a second air passage, wherein the second fuel opening and the filming surface of the second air passage are located in a radially outer wall of the second air passage,wherein the first air passage is located radially outward of the second air passage, andan air swirler is located in the second air passage upstream of the second fuel opening; andwherein the first air passage and the second air passage are configured to merge at a shear region for mixing fuel delivered through the first fuel opening with fuel delivered through the second fuel opening, wherein the shear region is upstream of a throat of the fuel injector. 16. The apparatus of claim 15, the fuel injector further including a third air passage, wherein the first air passage and third air passage merge at an intermixing region for intermixing a fuel film in the first air passage with an air traversing the third air passage. 17. A method comprising: providing a first fuel to a first air passage through a first aperture;atomizing the first fuel in the first air passage;wetting a surface of the first air passage opposite the first aperture as a result of the providing the first fuel to the first air passage, wherein the wetting the surface of the first air passage comprising forming a film of fuel on the surface of the first air passage;delivering a second fuel to a second air passage through an opening located in a radially outer wall of the second air passage, the first air passage located radially outward of the second air passage;filming the second fuel along a film surface in the second air passage to create a fuel film; swirling an air traversing the second air passage before the air reaches the opening located in the radially outer wall of the second air passage;shearing the fuel film created by the filming the second fuel along the film surface in the second air passage between an air traversing the first air passage and the air traversing the second air passage; and combusting the first fuel and the second fuel in a combustor of a gas turbine engine. 18. The method of claim 17, which further includes swirling the air traversing the first air passage at a location upstream of the location of the atomizing. 19. The method of claim 18, which further includes imparting a rotational flow component to the second fuel. 20. The method of claim 19, wherein the imparting the rotational flow component occurs upstream of the second air passage. 21. The method of claim 17, which further includes: swirling air through a third air passage; andconveying the film of fuel to a convergence of the air traversing the first air passage and the air traversing the third air passage.