Patent ID: 9163840
Filing Date: 2015-10-20
Classification: F02C,F23D,F23R

Abstract:
1. A gas turbine combustor comprising: a combustion chamber to which fuel and air are supplied; a first burner located on an upstream side of the combustion chamber, the first burner jetting fuel into the combustion chamber and jetting air into the combustion chamber in a swirling manner; a plurality of second burners arranged around the first burner, each of the second burners supplying a premixed gas of air and fuel to the combustion chamber; an annular bulkhead disposed between the first burner and the second burners, the annular bulkhead having an inclined surface formed to broaden toward the downstream side of the combustion chamber; and a plurality of air jet ports formed in the inclined surface of the annular bulkhead, each of the air jet ports being adapted to jet air into the combustion chamber, the air jet ports formed between the first burner and the plurality of second burners, wherein one of the second burners has more of the air jet ports than the remaining second burners; wherein if the number of the second burners arranged around the first burner is K, the number of the air jet ports provided is K×n+1 (n=1, 2, 3, . . . ).