Gas Turbine Combustor

Abstract

In a gas turbine combustor, mixing of a fuel and air is accelerated in a mixing chamber of a burner as well as in air introduction passages provided in a wall of the mixing chamber, whereby NOx emissions from premixed combustion are reduced while at the same time, ignition characteristics and flame propagation characteristics improve. The gas turbine combustor includes a plurality of combustors 10 , a spark plug 13 , and a cross-fire tube 15 that propagates a flame between the combustors 10 . Each combustor 10 includes the burner 30 equipped with a fuel nozzle and the mixing chamber wall 32 forming the mixing chamber 31 . A plurality of air introduction holes 35, 36 for introducing combustion air, along with the fuel from the fuel nozzle, into the mixing chamber 31 , are provided in the mixing chamber wall 32 . The combustion air and fuel jetted from the air introduction hole 35 into the mixing chamber 31 are mixed in the form of a mixture “m 1 ”, “m 2 ” and directed towards the spark plug 13 and the cross-fire tube 15.

What is claimed is: 
     
         1 . A gas turbine combustor, comprising:
 a plurality of combustors each for supplying to a gas turbine a combustion gas resulting from combustion of a mixture of a fuel and combustion air introduced from a compressor, and each including a burner;   a spark plug for igniting the mixture; and   a cross-fire tube for propagating between the combustors a flame formed by the combustion of the mixture; wherein:   the burner includes
 a mixing chamber wall for forming a mixing chamber which opens towards a downstream side in an axial direction of the combustor, 
 a fuel nozzle for supplying a fuel, and 
 a plurality of air introduction passages installed in the mixing chamber wall each for introducing combustion air, along with the fuel from the fuel nozzle, into the mixing chamber; and 
   flows of the combustion air and fuel jetted from the air introduction passages into the mixing chamber are directed towards at least one of the spark plug and the cross-fire tube.   
     
     
         2 . The gas turbine combustor according to  claim 1 , wherein:
 in the mixing chamber wall, the air introduction passages are arranged so as to form a first row and a second row adjacently to each other, in the axial direction or in the radial direction;   the air introduction passage for jetting the combustion air which flows towards the spark plug belongs to the first row; and   the air introduction passage for jetting the combustion air which flows towards the cross-fire tube belongs to the second row.   
     
     
         3 . The gas turbine combustor according to  claim 1 , further comprising:
 a central burner as the burner; and   a plurality of outer peripheral burners each disposed at an outer peripheral side relative to the central burner; wherein:   the central burner includes a central mixing chamber wall that is the mixing chamber wall forming a central mixing chamber which is the mixing chamber, and a central fuel nozzle as the fuel nozzle;   the outer peripheral burners each include an outer peripheral mixing chamber wall forming an outer peripheral mixing chamber which opens towards a downstream side in the axial direction, and an outer peripheral fuel nozzle for supplying a fuel to the outer peripheral mixing chamber;   in the central mixing chamber wall, the combustion air introduction passages are provided so as to form a first row and a second row adjacently to each other, in the axial direction;   the air introduction passage for jetting the combustion air which flows towards at least one of the spark plug and the cross-fire tube belongs to the first row; and   the combustion air jetted from the air introduction passage belonging to the second row flows towards an exit of the outer peripheral mixing chamber.   
     
     
         4 . The gas turbine combustor according to  claim 3 , wherein:
 the number of the air introduction passages configuring the second row in the central burner is an integral multiple of the number of the outer peripheral burners.   
     
     
         5 . The gas turbine combustor according to  claim 3 , wherein:
 the number of the air introduction passages configuring an upstream row of the first row and the second row in the axial direction is six,   the number of the air introduction passages configuring an downstream row of the first row and the second row is twelve, and   the number of the outer peripheral burners is four or six.   
     
     
         6 . The gas turbine combustor according to  claim 4 , wherein:
 the number of the air introduction passages configuring an upstream row of the first row and the second row in the axial direction is six,   the number of the air introduction passages configuring an downstream row of the first row and the second row is twelve, and   the number of the outer peripheral burners is four or six.