| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a highly-reliable gas turbine combustor that reduces NOx and ensures combustion stability. <P>SOLUTION: This gas turbine combustor includes: a combustion chamber supplied with fuel and air; a first burner located on the upstream side of the combustion chamber to jet fuel into the combustion chamber and jet swirling air into the combustion chamber; a plurality of second burners arranged around the first burner and supplying a premixed gas of air and fuel to the combustion chamber; an annular bulkhead disposed between the first burner and the second burners and having an inclined surface formed to expand toward the downstream side of the combustion chamber; and a plurality of air jet ports formed in the inclined surface of the annular bulkhead and adapted to jet air into the combustion chamber. If K second burners are arranged around the first burner, the K×n+1 (n=1, 2, 3, ...) air jet ports are provided. <P>COPYRIGHT: (C)2012,JPO&INPIT |
