| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor that avoids an overheat in a structure of the gas turbine combustor to maintain combustion stability and low-NOx combustion performance, in a gas turbine combustor that burns a fuel containing hydrogen in the fuel composition thereof. <P>SOLUTION: The gas turbine combustor includes: an air vent plate 54 positioned upstream a combustion chamber and having a plurality of air vents 55-1, 55-2, 55-3; and a plurality of multi-hole co-axial jet burners each constituted of a plurality of fuel nozzles 56 disposed concentrically with the air vents and feeding the fuel containing hydrogen in the fuel composition thereof to the air vents. The gas turbine combustor has: a structure in which a combustion chamber side surface of each multi-hole co-axial jet burner is inclined toward a central part from an outer circumference side so as to project on a side of the combustion chamber, and a central part of the burner is recessed as a concave shape that is inclined so as to be separated from the combustion chamber; and a structure of pushing back a circulating gas 43 circulating toward a stagnation region 49 generated in the vicinity of the burner central part, to a downstream side of the combustion chamber so that the circulating gas is separated from the burner, for instance, a cooling air vent in the burner central part. <P>COPYRIGHT: (C)2013,JPO&INPIT |
