{
  "$type": "site.standard.document",
  "description": "A gas turbine that can effectively cool an axial cavity between a stator blade and a rotor blade and a blade-end surface is provided. In a gas turbine in which a blade-count difference between stator-blade segments (17) of a second-stage stator blade and a third-stage stator blade is set to zero, a…",
  "path": "/patents/1005972",
  "publishedAt": "2012-01-25T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D1/04",
    "MITSUBISHI HEAVY IND LTD [JP]"
  ],
  "textContent": "A gas turbine that can effectively cool an axial cavity between a stator blade and a rotor blade and a blade-end surface is provided. In a gas turbine in which a blade-count difference between stator-blade segments (17) of a second-stage stator blade and a third-stage stator blade is set to zero, a relative position between the second-stage stator blade and the third-stage stator blade in the circumferential direction is set by clocking so that a wake flow produced by the stator-blade segments of the second-stage stator blade is guided to the leading edges of the stator-blade segments (17) of the third-stage stator blade within a range of 0% to 15% of the length in a span direction from a hub side of the stator-blade segments (17) of the third-stage stator blade.",
  "title": "GAS TURBINE"
}