Gas turbine combustor
Adhesion of particulate matters to the burner accompanying combustion in a lean-combustion gas turbine combustor is suppressed, and the structural reliability is improved. In a gas turbine combustor including: 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 includes a plurality of air holes for guiding compressed air to the combustion chamber, and a plurality of fuel nozzles that are 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, a plurality of small holes having opening diameters smaller than those of the air holes are provided through the air hole plate such that the plurality of small holes are positioned in an inner area of an innermost annular line of the air holes.
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 tubular liner, and includes a plurality of air holes for guiding compressed air to the combustion chamber, and
a plurality of fuel nozzles that are 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 plurality of fuel nozzles forming a plurality of concentric annular lines, wherein
a plurality of small holes having opening diameters smaller than opening diameters of the plurality of of air holes are provided through the air hole plate such that the plurality of small holes are positioned in an inner area of an innermost annular line of the plurality of air holes,
the plurality of small holes are opened through a surface facing the combustion chamber of the air hole plate, and
the plurality of small holes are provided densely in an inner area of the innermost annular row of air holes than in an outer area of the innermost annular row of air holes in the burner.
2. The gas turbine combustor according to claim 1 , comprising:
an air flow passage connected to the plurality of small holes.
3. The gas turbine combustor according to claim 1 , comprising:
a fuel flow passage connected to the plurality of small holes.
4. The gas turbine combustor according to claim 3 , further comprising:
an air flow passage connected to the plurality of small holes.
5. The gas turbine combustor according to claim 4 , wherein
a bypass hole branching off from the air holes is connected to the plurality of small holes.
6. The gas turbine combustor according to claim 1 , comprising
the burner as a pilot burner,
further comprising:
a plurality of main burners arranged so as to surround a circumference of the pilot burner.
7. The gas turbine combustor according to claim 6 , comprising:
a plurality of the burners as the pilot burner and the plurality of main burners arranged to surround the circumference of the pilot burner.