Gas turbine combustor and gas turbine

Abstract

Provided are a gas turbine combustor and a gas turbine, with which the amount of NOx exhaust emissions from a diffuse combustion-type duct burner can be reduced. A duct burner is provided with cylindrical fuel injection nozzles and air holes. The fuel injection nozzles are supported by an outside casing along eight axial centers included within a plane orthogonal to a center axis and arranged at equidistant intervals (45-degree intervals) in the circumferential direction. Sets of eight fuel injection nozzles are respectively constituted as single fuel injection nozzle rows, four fuel injection nozzle rows being arrayed at prescribed spacing along a direction of a center axis. The angular positions of the fuel injection nozzles are arrayed so as to be shifted by a half-pitch angle in opposing rows.

1 . A combustor for use with a gas turbine engine, for mixing and combusting a fuel with a compressed air introduced from a compressor and supplying a generated combustion exhaust gas to a gas turbine, comprising:
 a combustion cylinder forming a combustion chamber therein;   a premixed combustion type main burner disposed on an upstream side of the combustion cylinder; and   a plurality of diffusion combustion type reheating burners disposed on a downstream side of the main burner to extend through a peripheral wall of the combustion cylinder for injecting a fuel from the peripheral wall into the combustion chamber,   the plurality of reheating burners being aligned in a circumferential direction and an axial direction of the combustion cylinder.   
     
     
         2 . The combustor according to  claim 1 , wherein the plurality of reheating burners in neighborhood arrays are disposed in a staggered fashion in the circumferential direction. 
     
     
         3 . The combustor according to  claim 1 , comprising a fuel header configured to distribute the fuel to the plurality of reheating burners. 
     
     
         4 . The combustor according to  claim 1 , comprising
 a first fuel header configured to distribute a first fuel mainly composed of methane to a predetermined number of reheating burners among the plurality of reheating burners, and   a second fuel header configured to distribute a second fuel composed of a hydrogen gas or a hydrogen-containing gas to the remaining reheating burners.   
     
     
         5 . A gas turbine engine comprising the combustor according to  claim 1 . 
     
     
         6 . A gas turbine engine comprising the combustor according to  claim 2 . 
     
     
         7 . A gas turbine engine comprising the combustor according to  claim 3 . 
     
     
         8 . A gas turbine engine comprising the combustor according to  claim 4 . 
     
     
         1 . A combustor for use with a gas turbine engine, for mixing and combusting a fuel with a compressed air introduced from a compressor and supplying a generated combustion exhaust gas to a gas turbine, comprising:
 a combustion cylinder forming a combustion chamber therein;   a premixed combustion type main burner disposed on an upstream side of the combustion cylinder; and   a plurality of diffusion combustion type reheating burners disposed on a downstream side of the main burner to extend through a peripheral wall of the combustion cylinder for injecting a fuel from the peripheral wall into the combustion chamber,   the plurality of reheating burners being aligned in a circumferential direction and an axial direction of the combustion cylinder.   
     
     
         2 . The combustor according to  claim 1 , wherein the plurality of reheating burners in neighborhood arrays are disposed in a staggered fashion in the circumferential direction. 
     
     
         3 . The combustor according to  claim 1  or  2 , comprising a fuel header configured to distribute the fuel to the plurality of reheating burners. 
     
     
         4 . The combustor according to any one of  claims 1  to  3 , comprising
 a first fuel header configured to distribute a first fuel mainly composed of methane to a predetermined number of reheating burners among the plurality of reheating burners, and 
 a second fuel header configured to distribute a second fuel composed of a hydrogen gas or a hydrogen-containing gas to the remaining reheating burners. 
 
     
     
         5 . A gas turbine engine comprising the combustor according to any one of  claims 1  to  4 .