Fuel nozzle and swirler

Abstract

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

What is claimed is: 
     
         1 . A turbine engine comprising:
 a compressor section, combustor section, and turbine section in serial flow arrangement, defining a rotational axis and extending from forward to aft, with the combustor section including a fuel nozzle assembly comprising:
 a fuel nozzle defining a longitudinal axis and including an outer wall defining a fuel passage; 
 a radial swirler circumscribing the fuel nozzle and defining a swirler air passage, the radial swirler including a forward wall and an aft wall; 
 a vane extending across the swirler air passage between the forward wall and the aft wall; and 
 a secondary fuel passage passing through the forward wall, the vane, and the aft wall and exhausting to the swirler air passage from an outlet at the aft wall. 
   
     
     
         2 . The turbine engine of  claim 1 , wherein the secondary fuel passage is fluidly isolated from the fuel passage of the fuel nozzle within the fuel nozzle assembly. 
     
     
         3 . The turbine engine of  claim 2 , wherein the fuel nozzle terminates at a nozzle tip, and wherein the outlet for the secondary fuel passage is positioned forward of the nozzle tip. 
     
     
         4 . The turbine engine of  claim 1 , further including a nozzle cap positioned within the fuel passage. 
     
     
         5 . The turbine engine of  claim 4 , wherein the fuel nozzle terminates at a nozzle tip, and wherein the nozzle cap is spaced from the nozzle tip. 
     
     
         6 . The turbine engine of  claim 1 , wherein the fuel nozzle terminates at a nozzle tip. 
     
     
         7 . The turbine engine of  claim 6 , wherein the outlet for the secondary fuel passage is positioned forward of the nozzle tip. 
     
     
         8 . The turbine engine of  claim 1 , wherein the outlet is arranged perpendicular to an axis defined by the aft wall. 
     
     
         9 . The turbine engine of  claim 1 , wherein the outlet is arranged at an angle to an axis defined by the aft wall. 
     
     
         10 . The turbine engine of  claim 1 , wherein the angle is an axially aft angle. 
     
     
         11 . The turbine engine of  claim 1 , wherein the outlet has a tangential component to impart a swirling component to a secondary fuel exiting the secondary fuel passage. 
     
     
         12 . A fuel nozzle assembly comprising:
 a fuel nozzle defining a longitudinal axis and including an outer wall defining a fuel passage;   
       a radial swirler circumscribing the fuel nozzle and defining a swirler air passage, the radial swirler including a forward wall and an aft wall; 
       a vane extending across the swirler air passage between the forward wall and the aft wall; and 
       a secondary fuel passage passing through the forward wall, the vane, and the aft wall and exhausting to the swirler air passage from an outlet at the aft wall. 
     
     
         13 . The fuel nozzle assembly of  claim 12 , wherein the secondary fuel passage is fluidly isolated from the fuel passage of the fuel nozzle within the fuel nozzle assembly. 
     
     
         14 . The fuel nozzle assembly of  claim 13 , wherein the fuel nozzle terminates at a nozzle tip, and wherein the outlet for the secondary fuel passage is positioned forward of the nozzle tip. 
     
     
         15 . The fuel nozzle assembly of  claim 12 , further comprising a nozzle cap positioned within the fuel passage. 
     
     
         16 . The fuel nozzle assembly of  claim 15 , wherein the fuel nozzle terminates at a nozzle tip, and wherein the nozzle cap is spaced from the nozzle tip. 
     
     
         17 . The fuel nozzle assembly of  claim 16 , wherein the outlet for the secondary fuel passage is positioned forward of the nozzle tip.