Gas turbine combustor structure

Abstract

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO2 gas turbine which uses supercritical CO2 for a working fluid, a casing of the suprecritical CO2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

Dependencies are inferred from the claim text.