{
  "$type": "site.standard.document",
  "description": "A stationary blade (133) of a gas turbine (10), which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud (133c) of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks (32e, 34e, 36e, 38e) in an axial…",
  "path": "/patents/1090393",
  "publishedAt": "2004-01-14T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/02",
    "MITSUBISHI HEAVY IND LTD [JP]"
  ],
  "textContent": "A stationary blade (133) of a gas turbine (10), which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud (133c) of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks (32e, 34e, 36e, 38e) in an axial direction of the gas turbine. A concave portion (40) is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion (133i) which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.",
  "title": "Stationary blade in gas turbine and gas turbine comprising the same"
}