GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of reducing dispersion of flow rate of air passing through air holes by suppressing increase of pressure loss, in the gas turbine combustor having a plurality of fuel nozzles, and an air hole plate on which the plurality of air holes are formed, and allowing the combustion air to flow into a combustion chamber from the plurality of air holes by reversing a flowing direction of the combustion air at an upstream portion of the combustor.SOLUTION: A gas turbine combustor includes a combustor liner forming a combustion chamber, a plurality of fuel nozzles, an air hole plate having a plurality of air holes, and an outer cylinder and an end cover enclosing the combustor liner and the air hole plate. A surface at an air hole plate side, of the end cover is projected to an air hole plate side from an outer side in the radial direction, of the combustor toward a central side of the combustor. An outer peripheral side in the radial direction, of the end cover is preferably recessed to an end cover side.