Abstract: A gas turbine combustor includes inner and outer liners that are concentric and cylindrical, and an end liner closing between upstream ends thereof and forming a hollow cylindrical combustion chamber therein, and a swirling air flow forming device introducing combustion air about the end liner from outside and forming a swirling air flow, a fuel ejector ejecting fuel in the swirling direction to form a premixed swirling flow, and an igniter igniting the premixed swirling flow to form a tubular flame surface. The combustion chamber includes a primary combustion chamber, a secondary combustion chamber disposed downstream of the primary combustion chamber, and an annular restrictor reducing the outer diameter of the primary combustion chamber and disposed therebetween. A diluting air hole, supplying diluting air along a flow of the combustion gas passing through the restrictor, is disposed downstream of the restrictor in the inner liner.

Abstract: A gas turbine combustor is provided which can accomplish stable high-load combustion, high combustion efficiency, a low concentration of CO, and NOx in a small-sized combustion chamber. The gas turbine combustor includes an inner liner 12 and an outer liner 14 being concentric and cylindrical and an end liner 16 closing between upstream ends thereof and forms a hollow cylindrical combustion chamber 18 therein. The gas turbine combustor further includes a swirling air flow forming device 22 introducing combustion air 7a into the vicinity of the end liner in the combustion chamber 18 from the outside and forming a swirling air flow, a fuel ejector 24 ejecting fuel 8 in the swirling direction to form a premixed swirling flow, and an igniter 26 igniting the premixed swirling flow to form a tubular flame surface 11.