{
  "$type": "site.standard.document",
  "description": "A combustor structure 1 of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor 97 in a suprecritical CO gas turbine which uses supercritical CO for a working fluid, a casing of the suprecritical CO gas turbine. The combustor structure 1…",
  "path": "/patents/1406484",
  "publishedAt": "2025-09-17T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/26",
    "TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORP [JP]"
  ],
  "textContent": "A combustor structure 1 of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor 97 in a suprecritical CO gas turbine which uses supercritical CO for a working fluid, a casing of the suprecritical CO gas turbine. The combustor structure 1 includes a plurality of combustors 50. Each of the combustors 50 includes: a combustor liner 51 in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part 52 which is provided at an upstream end of the combustor liner 51 and supplies the fuel into the combustor liner; and an oxidant supply part 53 which is provided at the upstream end of the combustor liner 51 and supplies the oxidant into the combustor liner.",
  "title": "GAS TURBINE USING SUPERCRITICAL CO2"
}