Gas turbine combustor having main fuel valves independently adjustable
Provided is a gas turbine combustor that can achieve improvement of the combustion stability. A gas turbine combustor includes a pilot burner of the diffusion combustion type, a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner, a main burner of the premix combustion type arranged on an outer circumference side of the pilot burner, main flow control valves that regulate flow rates of fuel to be individually supplied to burner sectors into which the main burner is sectioned in a circumferential direction, and a controller configured to control the pilot flow control valve and the main flow control valves. The controller controls the main flow control valves such that, when fuel is to be supplied to all the burner sectors, a difference in fuel flow rate occurs between at least one burner sector and the other burner sectors among the burner sectors.
1. A gas turbine combustor comprising:
a pilot burner;
a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner;
a main burner of premix combustion type arranged on an outer circumference side of the pilot burner;
a plurality of main flow control valves that regulate flow rates of fuel to be individually supplied to a plurality of burner sectors into which the main burner is sectioned in a circumferential direction; and
a controller configured to control the pilot flow control valve and the plurality of main flow control valves,
a combination chamber arranged on a downstream side of the pilot burner and the main burner, wherein
the controller is configured to control the plurality of main flow control valves such that, when fuel is to be supplied to all of the plurality of burner sectors, a flow rate of at least one burner sector increases and a flow rate of another burner sector or other burner sectors decreases with respect to an average value of the fuel flow rates of the plurality of burner sectors, whereby a difference in fuel flow rate occurs among the plurality of burner sectors.
2. The gas turbine combustor according to claim 1 , wherein
the controller controls the plurality of main flow control valves such that, when fuel is to be supplied to all of the plurality of burner sectors, each fuel flow rate of the plurality of burner sectors increases and decreases alternately in the circumferential direction with respect to an average value of the fuel flow rates of the plurality of burner sectors.