{
  "$type": "site.standard.document",
  "description": "A combustion burner for a gas turbine, configured so that fuel is uniformly ejected from ejection holes to reduce the NOx generation of the gas turbine combustor. A combustion burner for a gas turbine, provided with: rotating vanes (20) for ejecting fuel from fuel ejection holes (23, 24) to air or…",
  "path": "/patents/998282",
  "publishedAt": "2012-09-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/22",
    "MITSUBISHI HEAVY IND LTD [JP]"
  ],
  "textContent": "A combustion burner for a gas turbine, configured so that fuel is uniformly ejected from ejection holes to reduce the NOx generation of the gas turbine combustor. A combustion burner for a gas turbine, provided with: rotating vanes (20) for ejecting fuel from fuel ejection holes (23, 24) to air or a mixture gas of air and fuel, which flows from the upstream side, and applying a swirling force to the air or the mixture gas to create a swirling mixture gas flow; and a nozzle (21) which have the rotating vanes (20) disposed in a radiating manner on the outer peripheral surface thereof and which have formed therein a first fuel flow path (26) for guiding the fuel to the fuel ejection holes (23, 24). The rotating vanes (20) have provided therein cavities (25) which communicate with the fuel ejection holes (23, 24), and at least two second fuel flow paths (27) are provided between each cavity (25) and the first fuel flow path (26) so as to extend in the axial direction.",
  "title": "COMBUSTION BURNER FOR GAS TURBINE"
}