System for supplying fuel to a combustor

Abstract

A system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber. A plurality of fuel nozzles are radially arranged across the combustor upstream from the combustion chamber to supply a swirling flow of fuel into the combustion chamber. A first fuel injector downstream from the plurality of fuel nozzles provides fluid communication for fuel to flow through the liner and into the combustion chamber. The first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.

What is claimed is: 
     
         1 . A system for supplying fuel to a combustor, comprising:
 a. a combustion chamber;   b. a liner that circumferentially surrounds at least a portion of the combustion chamber;   c. a plurality of fuel nozzles radially arranged across the combustor upstream from the combustion chamber, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;   d. a first fuel injector downstream from the plurality of fuel nozzles, wherein the first fuel injector provides fluid communication for fuel to flow through the liner and into the combustion chamber; and   e. wherein the first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.   
     
     
         2 . The system as in  claim 1 , wherein each fuel nozzle comprises a plurality of swirler vanes that extend radially between a center body and a shroud. 
     
     
         3 . The system as in  claim 1 , wherein the first fuel injector intersects the liner at a compound angle. 
     
     
         4 . The system as in  claim 1 , further comprising a second fuel injector downstream from the plurality of fuel nozzles, wherein the second fuel injector provides fluid communication for fuel to flow through the liner and into the combustion chamber, and wherein the second fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber. 
     
     
         5 . The system as in  claim 4 , wherein the second fuel injector is axially aligned substantially even with the first fuel injector. 
     
     
         6 . The system as in  claim 4 , wherein the second fuel injector is axially aligned in the combustion chamber downstream from the first fuel injector. 
     
     
         7 . The system as in  claim 4 , wherein the second fuel injector intersects the liner at a compound angle. 
     
     
         8 . The system as in  claim 1 , further comprising a flow sleeve that circumferentially surrounds at least a portion of the liner and a fuel plenum inside the flow sleeve in fluid communication with the first fuel injector. 
     
     
         9 . A system for supplying fuel to a combustor, comprising:
 a. a combustion chamber;   b. a liner that circumferentially surrounds at least a portion of the combustion chamber;   c. a plurality of fuel nozzles radially arranged across the combustor upstream from the combustion chamber, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;   d. a first set of fuel injectors circumferentially arranged around the liner downstream from the plurality of fuel nozzles, wherein the first set of fuel injectors provide fluid communication for fuel to flow through the liner and into the combustion chamber; and   e. wherein the first set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.   
     
     
         10 . The system as in  claim 9 , wherein each fuel nozzle comprises a plurality of swirler vanes that extend radially between a center body and a shroud. 
     
     
         11 . The system as in  claim 9 , wherein each fuel injector in the first set of fuel injectors intersects the liner at a compound angle. 
     
     
         12 . The system as in  claim 9 , further comprising a second set of fuel injectors circumferentially arranged around the liner downstream from the first set of fuel injectors, wherein the second set of fuel injectors provide fluid communication for fuel to flow through the liner and into the combustion chamber, and wherein the second set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber. 
     
     
         13 . The system as in  claim 12 , wherein the second set of fuel injectors are axially aligned in the combustion chamber downstream from the first set of fuel injectors. 
     
     
         14 . The system as in  claim 12 , wherein each fuel injector in the second set of fuel injectors intersects the liner at a compound angle. 
     
     
         15 . The system as in  claim 9 , further comprising a flow sleeve that circumferentially surrounds at least a portion of the liner and a fuel plenum inside the flow sleeve in fluid communication with the first set of fuel injectors. 
     
     
         16 . A gas turbine, comprising:
 a. a compressor;   b. a combustor downstream from the compressor;   c. a turbine downstream from the combustor;   d. a plurality of fuel nozzles radially arranged inside the combustor;   e. a combustion chamber downstream from the plurality of fuel nozzles, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;   f. a first set of fuel injectors circumferentially arranged around the combustion chamber downstream from the plurality of fuel nozzles, wherein the first set of fuel injectors provide fluid communication for fuel to flow into the combustion chamber; and   g. wherein the first set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.   
     
     
         17 . The gas turbine as in  claim 16 , wherein each fuel injector in the first set of fuel injectors intersects the liner at a compound angle. 
     
     
         18 . The gas turbine as in  claim 16 , further comprising a second set of fuel injectors circumferentially arranged around the combustion chamber downstream from the first set of fuel injectors, wherein the second set of fuel injectors provide fluid communication for fuel to flow into the combustion chamber, and wherein the second set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber. 
     
     
         19 . The gas turbine as in  claim 18 , wherein the second set of fuel injectors are axially aligned in the combustion chamber downstream from the first set of fuel injectors. 
     
     
         20 . The gas turbine as in  claim 18 , wherein each fuel injector in the second set of fuel injectors intersects the combustion chamber at a compound angle.