Gas turbine combustor and fuel supply method used for the same

摘要

An object of the invention is to provide a reliable gas turbine combustor that can satisfy lowered NOx and combustion stability. The gas turbine combustor includes a combustion chamber 8 to which fuel and air are supplied; a first burner 20 located on the upstream side of the combustion chamber 8, the first burner 20 jetting fuel into the combustion chamber 8 and jetting air into the combustion chamber 8 in a swirling manner; a plurality of second burners 30 arranged around the first burner 20 and supplying a premixed gas of air and fuel to the combustion chamber 8; an annular bulkhead 26 disposed between the first burner 20 and the second burners 30 and having an inclined surface formed to broaden toward the downstream side of the combustion chamber 8; and a plurality of air jet ports 27 formed in the inclined surface of the annular bulkhead 26 and adapted to jet air into the combustion chamber 8. If the number of the second burners 30 arranged around the first burner 20 is K, the number of the air jet ports 27 provided is K x n + 1 (n = 1, 2, 3, ···).