{
  "$type": "site.standard.document",
  "description": "A fuel delivery system (10) for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle (22), a variable critical flow nozzle (24), a first fuel nozzle (36) and a second fuel nozzle (38). The fixed critical flow nozzle (22) and the variable critical flow nozzle (24) are…",
  "path": "/patents/1003906",
  "publishedAt": "2012-03-28T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/228",
    "HAMILTON SUNDSTRAND CORP [US]"
  ],
  "textContent": "A fuel delivery system (10) for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle (22), a variable critical flow nozzle (24), a first fuel nozzle (36) and a second fuel nozzle (38). The fixed critical flow nozzle (22) and the variable critical flow nozzle (24) are connected to a fuel source (14) in parallel. The fixed critical flow nozzle has an orifice throat (42) with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat (58) with a variable effective cross-sectional area. The first fuel nozzle (36) is connected to the fixed critical flow nozzle (22) for delivering fuel to the gas turbine engine, and the second fuel nozzle (38) is connected to the variable critical flow nozzle (24) for delivering fuel to the gas turbine engine.",
  "title": "Critical flow nozzle for controlling fuel distribution and burner stability"
}