{
  "$type": "site.standard.document",
  "description": "The fan (11) for especially an aviation gas turbine engine has a supplementary rotor (18) positioned upstream of the fan rotor (13) with blades (19) which extend radially outwards from a hub and finish at a distance from the outer wall (16) of the fan flow passage. The supplementary rotor and fan…",
  "path": "/patents/1069403",
  "publishedAt": "2006-03-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K3/06",
    "MTU AERO ENGINES GMBH [DE]"
  ],
  "textContent": "The fan (11) for especially an aviation gas turbine engine has a supplementary rotor (18) positioned upstream of the fan rotor (13) with blades (19) which extend radially outwards from a hub and finish at a distance from the outer wall (16) of the fan flow passage. The supplementary rotor and fan rotor are constructed as separate rotors, whereby the supplementary rotor is driven at a higher RPM than the fan rotor. The transmission ratio between the supplementary rotor RPM and fan rotor RPM may be fixed or variable. An independent claim is included for especially an aviation gas turbine engine equipped with the aforesaid fan.",
  "title": "Fan for an aircraft engine"
}