Gas Turbine Combustor

Abstract

A gas turbine combustor includes: an inner casing; an outer casing; an annular flow path disposed between the inner casing and the outer casing; a fuel header; a plurality of fuel nozzles supported concentrically on the fuel header; an air hole plate having a plurality of air holes associated with the respective fuel nozzles; a guide having a wall portion and a bent portion; and an outer peripheral flow path defined between the outer peripheral surface of the air hole plate and the inner casing.

What is claimed is: 
     
         1 . A gas turbine combustor, comprising:
 an inner casing that defines thereinside a combustion chamber;   an outer casing disposed so as to cover the inner casing;   an annular flow path disposed between the inner casing and the outer casing, the annular flow path allowing high-pressure air to flowing therethrough;   a fuel header disposed downstream of the outer casing in a flow direction of the high-pressure air;   a plurality of fuel nozzles supported concentrically on the fuel header;   an air hole plate disposed downstream of the fuel nozzles in a flow direction of fuel, the air hole plate having a plurality of air holes associated with the respective fuel nozzles;   a guide including a wall portion that protrudes from an outer peripheral surface of the air hole plate further on an outer peripheral side of the inner casing and a bent portion formed into a convex shape protruding toward the outer casing and the fuel header and arcuately connected with the air hole on an outermost periphery in a radial direction of the air hole plate; and   an outer peripheral flow path defined between the outer peripheral surface of the air hole plate and the inner casing, the outer peripheral flow path supplying an outer peripheral portion of a part of the combustion chamber on a side of the air hole plate with the high-pressure air.   
     
     
         2 . The gas turbine combustor according to  claim 1 , further comprising:
 a spring seal disposed between the outer peripheral surface of the air hole plate and the inner casing, wherein   the spring seal has a hole formed therein, through which the high-pressure air can circulate.   
     
     
         3 . The gas turbine combustor according to  claim 1 , wherein:
 the air hole plate includes an extension disposed on an outer peripheral portion thereof, the extension extending from a wall surface on a side adjacent to the combustion chamber downstream in a flow direction of combustion gas, and   the outer peripheral flow path has an outlet formed to pass through the extension.   
     
     
         4 . The gas turbine combustor according to  claim 1 , wherein the annular flow path includes a flow path expanded portion having a flow path area increasing toward a downstream side in the flow direction of the high-pressure air. 
     
     
         5 . The gas turbine combustor according to  claim 1 , wherein the outer casing or the fuel header includes a curved surface portion curved to follow a profile of the bent portion. 
     
     
         6 . The gas turbine combustor according to  claim 1 , further comprising:
 a guide vane disposed between the guide in the annular flow path and the fuel header, wherein   the guide vane is disposed such that a rear edge portion thereof is disposed, with respect to a front edge portion thereof, on an inside in the radial direction of the air hole plate and on a side of the air hole on the outermost periphery of the air hole plate.   
     
     
         7 . The gas turbine combustor according to  claim 1 , further comprising:
 a supply flow path disposed between the air hole plate and the fuel header; and   an annular connecting member that separates the annular flow path from the supply flow path, wherein   the connecting member has a communication hole that provides communication between the annular flow path and the supply flow path.   
     
     
         8 . A gas turbine plant, comprising:
 a compressor that compresses air;   the gas turbine combustor according to  claim 1 , the gas turbine combustor mixing high-pressure air supplied from the compressor with fuel to burn a resultant mixture; and   a turbine rotatably driven by combustion gas supplied from the gas turbine combustor.