Gas Turbine Combustor
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.
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.