System and method for tube level air flow conditioning

Abstract

A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage.

1 . A system, comprising:
 a multi-tube fuel nozzle, comprising:
 a plurality of tubes, wherein each tube comprises:
 a first end; 
 a second end; 
 an annular wall disposed about a central passage, wherein the first end is configured to be disposed about a fuel injector; and 
 an air flow conditioner having a plurality of air ports disposed adjacent the first end, wherein the plurality of air ports extend through the wall into the central passage. 
 
   
     
     
         2 . The system of  claim 1 , wherein the plurality of air ports are circumferentially arranged about the annular wall. 
     
     
         3 . The system of  claim 2 , wherein the plurality of air ports comprises a first set of air ports and a second set of air ports, wherein the second set of air ports are located downstream of the first set of air ports relative to the first end. 
     
     
         4 . The system of  claim 3 , wherein a first total area of each air port of the first set of air ports is larger than a second total area of each air port of the second set of air ports. 
     
     
         5 . The system of  claim 3 , wherein the first set of air ports comprises a first row and a second row of air ports circumferentially arranged about the annular wall, and the first row of air ports are offset from the second row of air ports in a circumferential direction. 
     
     
         6 . The system of  claim 5 , wherein the second set of air ports comprises a third row and a fourth row of air ports circumferentially arranged about the annular wall, and the third row of air ports are offset from the fourth row of air ports in the circumferential direction. 
     
     
         7 . The system of  claim 3 , wherein the first set of air ports is configured to guide air flow in a radial direction into the central passage. 
     
     
         8 . The system of  claim 7 , wherein the second set of air ports is configured to guide the air with a swirling motion about a central axis of the central passage. 
     
     
         9 . The system of  claim 1 , wherein the plurality of air ports comprise a plurality of sizes, shapes, angles, spacings, or any combination thereof. 
     
     
         10 . The system of  claim 1 , wherein each tube of the plurality of tubes is configured to receive an equal distribution of air flow via the air flow conditioner. 
     
     
         11 . The system of  claim 1 , comprising a gas turbine engine or a combustor having the multi-tube fuel nozzle. 
     
     
         12 . A system, comprising:
 a combustor end cover assembly;   a multi-tube fuel nozzle coupled to the combustor end cover assembly, comprising:
 a retainer plate; and 
 a plurality of tubes disposed between the end cover assembly and the retainer plate, wherein each tube comprises:
 a first end adjacent the end cover assembly; 
 a second end adjacent the retainer plate; 
 an annular wall disposed about a central passage, wherein the first end is configured to be disposed about a fuel injector; and 
 an air flow conditioner having a plurality of air ports disposed adjacent the first end, wherein the plurality of air ports extend through the wall into the central passage. 
 
   
     
     
         13 . The system of  claim 12 , wherein each tube of the plurality of tubes is configured to be individually removed from or installed between the end cover assembly and the retainer plate. 
     
     
         14 . The system of  claim 13 , wherein the retainer plate is configured to be removed from the multi-tube fuel nozzle by sliding the retainer plate along the plurality of tubes from the first end to the second end of each tube upon removal of the end cover assembly. 
     
     
         15 . The system of  claim 12 , wherein the plurality of air ports are circumferentially arranged about the annular wall. 
     
     
         16 . The system of  claim 15 , wherein the plurality of air ports comprises a first set of air ports and a second set of air ports, wherein the second set of air ports are located downstream of the first set of air ports relative to the first end. 
     
     
         17 . The system of  claim 16 , wherein a first total area of each air port of the first set of air ports is larger than a second total area of each air port of the second set of air ports. 
     
     
         18 . The system of  claim 16 , wherein the first set of air ports is configured to guide air flow in a radial direction into the central passage. 
     
     
         19 . The system of  claim 18 , wherein the second set of holes is configured to guide the air with a swirling motion about a central axis of the central passage. 
     
     
         20 . A system, comprising:
 a combustor end cover assembly;   a multi-tube fuel nozzle coupled to the combustor end cover assembly, comprising:
 a retainer plate; and 
 a tube disposed between the end cover assembly and the retainer plate, wherein the tube comprises:
 a first end adjacent the end cover assembly; 
 a second end adjacent the retainer plate; 
 an annular wall disposed about a central passage, wherein the first end is configured to be disposed about a fuel injector; and 
 an air flow conditioner having a plurality of air ports disposed adjacent the first end, wherein the plurality of air ports extend through the wall into the central passage.