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A fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream from the fuel injector and a second

A fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream from the fuel injector and a second swirler wherein the second swirler is located downstream from the fuel injector. The plurality of discrete plain jet orifices are situated between the highly swirling airstreams generated by the two radial swirlers. The distributed injection of the fuel between two highly swirling airstreams results in rapid and effective mixing to the desired fuel-air ratio and prevents the formation of local hot spots in the combustor primary zone. A combustor and a gas turbine engine comprising the fuel-air mixer of the present invention are also provided as well as a method using the fuel-air mixer of the present invention.

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The invention claimed is: 1. A fuel-air mixer comprising: a fuel injector having a plurality of discrete plain jet orifices; a first swirler located upstream from the discrete plain jet orifices; and a second swirler located downstream from the discrete plain jet orifices; and wherein the first swi

The invention claimed is: 1. A fuel-air mixer comprising: a fuel injector having a plurality of discrete plain jet orifices; a first swirler located upstream from the discrete plain jet orifices; and a second swirler located downstream from the discrete plain jet orifices; and wherein the first swirler and the second swirler are adjacent to the discrete plain jet orifices and the fuel injector further comprises a fuel delivery line located between swirler airflow passages of the first swirler. 2. The fuel-air mixer of claim 1 wherein the fuel injector is an annular fuel injector. 3. The fuel-air mixer of claim 1 wherein the plurality of discrete plain jet orifices are arranged circumferentially around the fuel injector. 4. The fuel-air mixer of claim 1 wherein the first and second swirlers have a co-swirled orientation. 5. The fuel-air mixer of claim 1 wherein the first and second swirlers have a counter-swirled orientation. 6. The fuel-air mixer of claim 1 wherein the first swirler comprises aerodynamic vanes, flat vanes or tangentially-oriented discretely drilled holes. 7. The fuel-air mixer of claim 1 wherein the second swirler comprises aerodynamic vanes, flat vanes or tangentially-oriented discretely drilled holes. 8. The fuel-air mixer of claim 1 wherein the first swirler is a radial swirler. 9. The fuel-air mixer of claim 1 wherein the second swirier is a radial swirler. 10. The fuel-air mixer of claim 1 wherein the fuel-air mixer further comprises a swirler exit throat downstream of the second swirler and a swirler exit quarl downstream of the swirler exit throat. 11. The fuel-air mixer of claim 10 wherein the swirler exit quarl is either converging, diverging or of a constant diameter relative to the swirler exit throat. 12. A fuel-air wiser for use in a combustion chamber of a gas turbine engine, the fuel-air mixer comprising: an annular fuel injector having a fuel delivery line fluidly connected to an annular fuel distribution manifold, wherein the annular fuel distribution manifold is fluidly connected to a plurality of discrete plain jet orifices and a first radial swirler wherein the first swirler is located upstream from the discrete plain jet orifices and wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler; and a secondary swirler assembly comprising a second radial swirler wherein the second swirler is located downstream from the discrete plain jet orifices, a swirler exit throat downstream of to second swirler and a swirler exit quarl downstream of the swirler exit throat. 13. The fuel-air mixer of claim 12 wherein the first and second swirlers have a co-swirled orientation. 14. The fuel-air mixer of claim 12 wherein the first and second swirlers have a counter-swirled orientation. 15. The fuel-air mixer of claim 12 wherein the first and second swirlers independently comprise aerodynamic vanes, flat vanes or tangentially-oriented discretely drilled holes. 16. The fuel-air mixer of claim 12 wherein the plurality of discrete plain jet orificess are oriented radially outward and tangentially counter to air delivered by the second swirler. 17. A combustor comprising a fuel-air mixer, the fuel-air mixer comprising: an annular fuel injector having a fuel delivery line fluidly connected to an annular fuel distribution manifold, wherein the annular fuel distribution manifold is fluidly connected to a plurality of discrete plain jet orifices and a first radial swirler wherein the first swirler is located upstream from the discrete plain jet orifices and wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler and a secondary swirler assembly comprising a second radial swirler wherein the second swirler is located downstream from the discrete plain jet orifices, a swirler exit throat downstream of the second swirler and a swirler exit quarl downstream of the swirler exit throat. 18. The combustor of claim 17 wherein the fuel-air mixer can be removed from the combustor. 19. The combustor of claim 17 wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler. 20. The combustar of claim 17 wherein the swirler exit quarl is either converging, diverging or of a constant diameter relative to the swirler exit throat. 21. A gas turbine engine having a combustor comprising a fuel-air mixer, the fuel-air mixer comprising: an annular fuel injector having a fuel delivery line fluidly connected to an annular fuel distribution manifold, wherein the annular fuel distribution manifold is fluidly connected to a plurality of discrete plain jet orifices; a first radial swirler wherein the first swirler is located upstream from the discrete plain jet orifices and wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler, a second radial swirler wherein the second swirler is located downstream from the discrete plain jet orifices; a swirler exit throat downstream of the second swirler; and a swirler exit quarl downstream of the swirler exit throat. 22. The gas turbine engine of claim 21 wherein the engine is a lean direct injection gas turbine engine. 23. The gas turbine engine of claim 21 wherein the engine is a rich burn-quick-quench-lean-burn engine.