Gas Turbine Combustor

Abstract

To suppress occurrence of combustion oscillation in a lean-combustion gas turbine combustor, and to improve the structural reliability. In a gas turbine combustor including: a tubular liner that forms a combustion chamber; and a burner having an air hole plate that is arranged at an inlet of the liner and that is provided with a plurality of air holes for guiding compressed air to the combustion chamber, and a plurality of fuel nozzles arranged on a side opposite to the combustion chamber with the air hole plate being sandwiched therebetween, the plurality of fuel nozzles each injecting a fuel toward a corresponding air hole, the air holes and the fuel nozzles forming a plurality of concentric annular lines, an orifice is provided on a fuel flow passage of each of the plurality of fuel nozzles, the plurality of fuel nozzles are grouped into a plurality of nozzle groups, and axial positions of the orifices are different between the nozzle groups.

What is claimed is: 
     
         1 . A gas turbine combustor comprising:
 a tubular liner that forms a combustion chamber; and   a burner including
 an air hole plate that is arranged at an inlet of the liner and that is provided with a plurality of air holes for guiding compressed air to the combustion chamber, and 
 a plurality of fuel nozzles arranged on a side opposite to the combustion chamber with the air hole plate being sandwiched therebetween, the plurality of fuel nozzles each injecting a fuel toward a corresponding air hole, 
 the air holes and the fuel nozzles forming a plurality of concentric annular lines, wherein 
   the plurality of fuel nozzles each include an orifice on a fuel flow passage, and are grouped into a plurality of nozzle groups, and   axial positions of the orifices are different between the nozzle groups.   
     
     
         2 . The gas turbine combustor according to  claim 1 , wherein
 fuel nozzles grouped into a same nozzle group belong to a same annular line, and the axial positions of the orifices of the fuel nozzles belonging to the same annular line coincide with each other.   
     
     
         3 . The gas turbine combustor according to  claim 1 , further comprising:
 a plurality of fuel cavities that supply a fuel separately to a plurality of fuel nozzles belonging to corresponding annular lines, wherein   the annular lines are grouped into a plurality of areas in a circumferential direction,   fuel nozzles grouped into a same nozzle group belong to a same area, and   fuel nozzles including orifices at different axial positions are mixedly present in a same annular line.   
     
     
         4 . The gas turbine combustor according to  claim 1 , wherein
 opening diameters of orifices belonging to an innermost annular line are larger than opening diameters of orifices belonging to an outermost annular line.   
     
     
         5 . The gas turbine combustor according to  claim 1 , further comprising:
 a plurality of the burners.