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 ; characterized in that the gas turbine combustor comprises: a guide including a wall portion that protrudes from an outer peripheral surface of the air hole plate further than 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 those of said plurality of air holes that are arranged 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 . 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 ; characterized in that the gas turbine combustor comprises: a guide including a wall portion that protrudes from an outer peripheral surface of the air hole plate further than 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 those of said plurality of air holes that are arranged 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 . a guide including a wall portion that protrudes from an outer peripheral surface of the air hole plate further than 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 those of said plurality of air holes that are arranged 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 . <EOS>