Fuel-air mixer assembly for use in a combustor of a turbine engine

Abstract

A fuel-air mixer assembly that includes a mixer portion, and a flare cup portion coupled to the mixer portion. The flare cup portion includes a side wall that including an inlet opening and a discharge opening defined therein. The side wall is oriented such that the discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.

What is claimed is: 
     
         1 . A fuel-air mixer assembly for use in a combustor, said fuel-air mixer assembly comprising:
 a mixer portion; and   a flare cup portion coupled to said mixer portion, said flare cup portion comprising a side wall that comprises an inlet opening and a discharge opening defined therein, wherein said side wall is oriented such that said discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.   
     
     
         2 . The assembly in accordance with  claim 1 , wherein said discharge opening is defined by a major axis and a minor axis oriented perpendicularly relative to each other, the major axis longer than the minor axis. 
     
     
         3 . The assembly in accordance with  claim 2 , wherein said side wall is divergently oriented relative to the centerline of the fuel-air mixer assembly at opposing ends of the major axis, said side wall oriented at an angle equal to or less than about 60 degrees relative to the centerline. 
     
     
         4 . The assembly in accordance with  claim 1 , wherein said mixer portion comprises a discharge end coupled to said flare cup portion at said inlet opening, said inlet opening and said discharge end both axi-symmetrically shaped relative to the centerline of the fuel-air mixer assembly. 
     
     
         5 . The assembly in accordance with  claim 1 , wherein said mixer portion comprises a discharge end coupled to said flare cup portion at said inlet opening, said inlet opening and said discharge end both axi-asymmetrically shaped relative to the centerline of the fuel-air mixer assembly. 
     
     
         6 . The assembly in accordance with  claim 1 , wherein said mixer portion comprises first swirler vanes and second swirler vanes arranged circumferentially within said mixer portion relative to the centerline, wherein said first swirler vanes are configured to direct airflow into said mixer portion in a different direction than said second swirler vanes. 
     
     
         7 . The assembly in accordance with  claim 1  further comprising a ferrule portion coupled to said mixer portion, said ferrule portion comprising first purge holes and second purge holes defined therein and arranged circumferentially relative to the centerline, wherein said first purge holes are sized smaller than said second purge holes. 
     
     
         8 . The assembly in accordance with  claim 1 , wherein said flare cup portion comprises a cylindrical section, a flared section, and a transition section defined therebetween. 
     
     
         9 . A combustor for use in a turbine engine, said combustor comprising:
 a fuel nozzle assembly; and   a fuel-air mixer assembly comprising:
 a mixer portion configured to receive fuel from said fuel nozzle assembly; and 
 a flare cup portion coupled to said mixer portion, said flare cup portion comprising a side wall that comprises an inlet opening and a discharge opening defined therein, wherein said side wall is oriented such that said discharge opening is axi-asymmetrically shaped relative to a centerline of said fuel-air mixer assembly. 
   
     
     
         10 . The combustor in accordance with  claim 9 , wherein said discharge opening is defined by a major axis and a minor axis oriented perpendicularly relative to each other, the major axis longer than the minor axis. 
     
     
         11 . The combustor in accordance with  claim 10 , wherein said fuel-air mixer assembly is oriented within the combustor such that the major axis is oriented tangentially relative to a circumference of the turbine engine. 
     
     
         12 . The combustor in accordance with  claim 10 , wherein said side wall is divergently oriented relative to the centerline of said fuel-air mixer assembly at opposing ends of the major axis, said side wall oriented at an angle equal to or less than about 60 degrees relative to the centerline. 
     
     
         13 . The combustor in accordance with  claim 9 , wherein said mixer portion comprises a discharge end coupled to said flare cup portion at said inlet opening, said inlet opening and said discharge end both axi-symmetrically shaped relative to the centerline of said fuel-air mixer assembly. 
     
     
         14 . The combustor in accordance with  claim 9 , wherein said mixer portion comprises a discharge end coupled to said flare cup portion at said inlet opening, said inlet opening and said discharge end both axi-asymmetrically shaped relative to the centerline of said fuel-air mixer assembly. 
     
     
         15 . The combustor in accordance with  claim 9 , wherein said mixer portion comprises first swirler vanes and second swirler vanes arranged circumferentially within said mixer portion relative to the centerline, wherein said first swirler vanes are configured to direct airflow into said mixer portion in a different direction than said second swirler vanes. 
     
     
         16 . A turbine engine comprising:
 a combustor comprising a fuel nozzle assembly and a fuel-air mixer assembly coupled to said fuel nozzle assembly, said fuel-air mixer assembly comprising:
 a mixer portion configured to receive fuel from said fuel nozzle assembly; and 
 a flare cup portion coupled to said mixer portion, said flare cup portion comprising a side wall that comprises an inlet opening and a discharge opening defined therein, wherein said side wall is oriented such that said discharge opening is axi-asymmetrically shaped relative to a centerline of said fuel-air mixer assembly. 
   
     
     
         17 . The turbine engine in accordance with  claim 16 , wherein said discharge opening is defined by a major axis and a minor axis oriented perpendicularly relative to each other, the major axis longer than the minor axis. 
     
     
         18 . The turbine engine in accordance with  claim 17 , wherein said side wall is divergently oriented relative to the centerline of said fuel-air mixer assembly at opposing ends of the major axis, said side wall oriented at an angle equal to or less than about 60 degrees relative to the centerline. 
     
     
         19 . The turbine engine in accordance with  claim 16 , wherein said mixer portion comprises first swirler vanes and second swirler vanes arranged circumferentially within said mixer portion relative to the centerline, wherein said first swirler vanes are configured to direct airflow into said mixer portion in a different direction than said second swirler vanes. 
     
     
         20 . The turbine engine in accordance with  claim 16  further comprising a ferrule portion coupled to said mixer portion, said ferrule portion comprising first purge holes and second purge holes defined therein and arranged circumferentially relative to the centerline, wherein said first purge holes are sized differently than said second purge holes.