Radial-radial-axial swirler assembly

Abstract

A swirler assembly for use in a combustor includes a first air swirler having a first swirler vane assembly, a second air swirler adjacent the first air swirler and having a second swirler vane assembly, and a ferrule coupled to the first air swirler and the second air swirler. The ferrule includes a ferrule swirler having a plurality of vanes. The first swirler vane assembly is configured to generate a first radial rotating airflow, and the second swirler vane assembly is configured to generate a second radial rotating airflow. The plurality of vanes of the ferrule swirler are configured to generate a ferrule axial airflow to interact with and mix to with the first radial rotating airflow and the second radial rotating airflow.

1 . A swirler assembly for use in a combustor, the swirler assembly comprising:
 a first air swirler having a first swirler vane assembly, wherein the first swirler vane assembly is configured to generate a first radial rotating airflow, the first radial rotating airflow rotating in a first direction;   a second air swirler adjacent the first air swirler and having a second swirler vane assembly, wherein the second swirler vane assembly is configured to generate a second radial rotating airflow, the second radial rotating airflow rotating in a second direction opposite to the first direction; and   a ferrule coupled to the first air swirler and the second air swirler, the ferrule comprising a ferrule swirler having a plurality of vanes, wherein the plurality of vanes of the ferrule swirler are configured to generate a ferrule axial airflow having a swirl to interact with and to mix with the first radial rotating airflow and the second radial rotating airflow.   
     
     
         2 . The swirler assembly according to  claim 1 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in an anti-clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radial rotating airflow in a clockwise direction or an anti-clockwise direction. 
     
     
         3 . The swirler assembly according to  claim 1 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in a clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radial rotating airflow in an anti-clockwise direction or a clockwise direction. 
     
     
         4 . The swirler assembly according to  claim 1 , wherein the plurality of vanes of the ferrule swirler are configured so that the ferrule axial airflow rotates in a same direction of the first radial rotating airflow or the same direction of the second radial rotating airflow. 
     
     
         5 . The swirler assembly according to  claim 1 , wherein the ferrule axial airflow forms an angle relative to a longitudinal axis of the swirler assembly between zero degree and sixty degrees. 
     
     
         6 . The swirler assembly according to  claim 1 , wherein the ferrule is movable radially in a direction generally perpendicular to a longitudinal axis of the swirler assembly. 
     
     
         7 . The swirler assembly according to  claim 1 , wherein the ferrule axial airflow interacting with the first radial rotating airflow and the second radial rotating airflow enables controlling swirler flow aerodynamics. 
     
     
         8 . A fuel-air mixer assembly for use in a combustor, the fuel-air mixer assembly comprising:
 (A) a first air swirler having a first swirler vane assembly, the first swirler vane assembly being configured to generate a first radial rotating airflow, the first radial rotating airflow rotating in a first direction;   (B) a second air swirler adjacent the first air swirler and having a second swirler vane assembly, the second swirler vane assembly being configured to generate a second radial rotating airflow, the second radial rotating airflow rotating in a second direction opposite to the first direction; and   (C) a ferrule coupled to the first air swirler and the second air swirler, the ferrule comprising:
 (a) a fuel nozzle configured to generate a fuel jet, and 
 (b) a ferrule swirler having a plurality of vanes, the plurality of vanes of the ferrule swirler being configured to generate a ferrule axial airflow having a swirl to interact with and to mix with the first radial rotating airflow and the second radial rotating airflow to generate an airflow vortex, 
   wherein the fuel jet is directed to interact with the airflow vortex to generate a controlled fuel-air mixture.   
     
     
         9 . The fuel-air mixer assembly according to  claim 8 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in an anti-clockwise direction, and the second swirler vane assembly is configured to turn the second radial rotating airflow in a clockwise direction or an anti-clockwise direction. 
     
     
         10 . The fuel-air mixer assembly according to  claim 8 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in a clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radial rotating airflow in an anti-clockwise direction or a clockwise direction. 
     
     
         11 . The fuel-air mixer assembly according to  claim 8 , wherein the plurality of vanes of the ferrule swirler are configured so that the ferrule axial airflow rotates in a same direction of the first radial rotating airflow or a same direction of the second radial rotating airflow. 
     
     
         12 . The fuel-air mixer assembly according to  claim 8 , wherein the ferrule axial airflow forms an angle relative to a longitudinal axis of the fuel-air mixer assembly between zero degree and sixty degrees. 
     
     
         13 . The fuel-air mixer assembly according to  claim 8 , wherein the ferrule is movable radially in a direction generally perpendicular to a longitudinal axis of the fuel-air mixer assembly. 
     
     
         14 . The fuel-air mixer assembly according to  claim 8 , wherein the ferrule axial airflow interacting with the first radial rotating airflow and the second radial rotating airflow enables controlling swirler flow aerodynamics. 
     
     
         15 . A turbine engine comprising:
 a combustor comprising a fuel-air mixer assembly and a fuel ignition assembly, the fuel-air mixer assembly comprising:   (A) a first air swirler having a first swirler vane assembly, the first swirler vane assembly being configured to generate a first radial rotating airflow, the first radial rotating airflow rotating in a first direction;   (B) a second air swirler adjacent the first air swirler and having a second swirler vane assembly, the second swirler vane assembly being configured to generate a second radial rotating airflow, the second radial rotating airflow rotating in a second direction opposite to the first direction; and   (C) a ferrule coupled to the first air swirler and the second air swirler, the ferrule comprising:
 (a) a fuel nozzle configured to generate a fuel jet, and 
 (b) a ferrule swirler having a plurality of vanes, the plurality of vanes of the ferrule swirler being configured to generate a ferrule axial airflow having a swirl to interact with and to mix with the first radial rotating airflow and the second radial rotating airflow to generate an airflow vortex, 
   wherein the fuel jet is directed to interact with the airflow vortex to generate a controlled fuel-air mixture for ignition by the fuel ignition assembly.   
     
     
         16 . The turbine engine according to  claim 15 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in an anti-clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radial rotating airflow in a clockwise direction or an anti-clockwise direction. 
     
     
         17 . The turbine engine according to  claim 15 , wherein the first swirler vane assembly is configured to turn the first radial rotating airflow in a clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radial rotating airflow in an anti-clockwise direction or a clockwise direction. 
     
     
         18 . The turbine engine according to  claim 15 , wherein the plurality of vanes of the ferrule swirler are configured so that the ferrule axial airflow rotates in a same direction of the first radial rotating airflow or a same direction of the second radial rotating airflow. 
     
     
         19 . The turbine engine according to  claim 15 , wherein the ferrule axial airflow forms an angle relative to a longitudinal axis of the fuel-air mixer assembly between zero degree and sixty degrees. 
     
     
         20 . The turbine engine according to  claim 15 , wherein the ferrule is movable radially in a direction generally perpendicular to a longitudinal axis of the fuel-air mixer assembly.