{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "A gas turbine generally comprises a compressor, a combustor and a turbine body operatively connected to the compressor through a rotation shaft, and the turbine body is composed of a plurality of rotors formed with turbine discs and movable blades which are arranged in plural stages along an axial…",
  "path": "/patents/1081719",
  "publishedAt": "2004-12-15T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/02",
    "TOSHIBA KK [JP]"
  ],
  "textContent": "A gas turbine generally comprises a compressor, a combustor and a turbine body operatively connected to the compressor through a rotation shaft, and the turbine body is composed of a plurality of rotors formed with turbine discs and movable blades which are arranged in plural stages along an axial direction of the turbine body, in which a rear shaft (16) is connected to a downstream side of a final stage disc of the turbine discs (17) so as to extend rearward from the final stage turbine disc (17) and supported by means of a bearing. The rear shaft (16) is formed with a cooling medium supply passage (18) for supplying a cooling medium to the turbine disc (17) and a cooling medium recovery passage (19) for recovering the cooling medium from the turbine disc (17), and a further cooling medium passage (21) is formed between the rear shaft (16) and either one of the cooling medium supply passage (18) and the cooling medium recovery passage (19).",
  "title": "Gas turbine rotor cooling"
}