Combustor Fuel Nozzle Structure

Abstract

A fuel nozzle including a plurality of fuel lines is provided, which has low thermal stress caused by a temperature difference between fuel and combustion air which are passed through the fuel nozzle, and also a gas turbine combustor using the fuel nozzle is provided. The fuel nozzle includes a plurality of channels including a first channel through which either fuel or combustion air is passed, and a second channel through which either fuel or combustion air is passed and which is distinct from the first channel. Of components of the fuel nozzle, a single-piece component makes up at least a region where the first channel and the second channel are placed.

What is claimed is: 
     
         1 . A fuel nozzle, comprising a plurality of channels including:
 a first channel through which either fuel or combustion air is passed; and   a second channel through which either fuel or combustion air is passed and which is distinct from the first channel,   wherein the fuel nozzle includes components, and a single-piece component of the components of the fuel nozzle makes up at least a region where the first channel and the second channel are placed.   
     
     
         2 . The fuel nozzle according to  claim 1 ,
 wherein each of the first channel and the second channel is divided into a plurality of sections and arranged in a circumferential direction of the fuel nozzle.   
     
     
         3 . The fuel nozzle according to  claim 1 ,
 wherein the combustion air is passed through the first channel, and   the fuel of a lower temperature than that of the combustion air is passed through the second channel.   
     
     
         4 . The fuel nozzle according to  claim 1 ,
 wherein, of the first channel and the second channel, only the first channel is disposed in proximity to a distal end of the fuel nozzle, and   a region where only the first channel is placed is joined to the region where the first channel and the second channel are placed.   
     
     
         5 . The fuel nozzle according to  claim 4 ,
 wherein the region where only the first channel is placed is joined to the region where the first channel and the second channel are placed, by either welding or Hot Isostatic Pressing (HIP) technique.   
     
     
         6 . A gas turbine combustor, comprising:
 a combustor liner that essentially makes up a combustion chamber in which a gas mixture of fuel and combustion air is burned;   a transition piece through which combustion gases are directed from the combustion chamber toward a turbine;   a pilot nozzle that supplies the fuel and the combustion air into the combustion chamber; and   a plurality of main nozzles that are arranged around the pilot nozzle to supply the fuel and the combustion air into the combustion chamber,   wherein the pilot nozzle has:
 a first channel through which either the fuel or the combustion air is passed; and 
 a second channel through which either the fuel or the combustion air is passed and which is distinct from the first channel, and 
   the pilot nozzle includes components, and a single-piece component of the components of the pilot nozzle makes up at least a region where the first channel and the second channel are placed.   
     
     
         7 . The gas turbine combustor according to  claim 6 ,
 wherein each of the first channel and the second channel is divided into a plurality of sections and arranged in a circumferential direction of the pilot nozzle.   
     
     
         8 . The gas turbine combustor according to  claim 6 ,
 wherein the combustion air is passed through the first channel, and   the fuel of a lower temperature than that of the combustion air is passed through the second channel.   
     
     
         9 . The gas turbine combustor according to  claim 6 ,
 wherein, of the first channel and the second channel, only the first channel is disposed in proximity to a distal end of the pilot nozzle, and   a region where only the first channel is placed is joined to the region where the first channel and the second channel are placed.   
     
     
         10 . The gas turbine combustor according to  claim 9 ,
 wherein the region where only the first channel is placed is joined to the region where the first channel and the second channel are placed, by either welding or Hot Isostatic Pressing (HIP) technique.