A combustor structure 1 of an embodiment includes: a plurality of combustors 50; a rear liner 60 which guides a combustion gas from the plurality of combustors 50 to a downstream side; and a scroll 70 which guides the combustion gas from the rear liner 60 in an axial direction and a circumferential direction of a turbine rotor 97. Each of the combustors 50 includes: a combustor liner 51; a fuel supply part 52 which supplies fuel into the combustor liner; and an oxidant supply part 53 which supplies a swirling flow of an oxidant from the circumference of the fuel supply part 52 into the combustor liner. The plurality of combustors 50 include: the combustor 50 in which a swirling direction of the swirling flow of the oxidant is clockwise; and the combustor 50 in which a swirling direction of the swirling flow of the oxidant is counterclockwise.