{
  "$type": "site.standard.document",
  "description": "A fan (12) for a turbofan gas turbine engine comprises a rotor hub (36) and a plurality of radially extending fan blades (20) integral with the hub (36) to form an integrally bladed rotor. Each fan blade (20) defines a leading edge (34). A hub radius (R HUB ) is the radius of the leading edge (34)…",
  "path": "/patents/974062",
  "publishedAt": "2014-06-04T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B23K20/129",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A fan (12) for a turbofan gas turbine engine comprises a rotor hub (36) and a plurality of radially extending fan blades (20) integral with the hub (36) to form an integrally bladed rotor. Each fan blade (20) defines a leading edge (34). A hub radius (R HUB ) is the radius of the leading edge (34) at the hub (36) relative to a centerline of the fan. A tip radius (R TIP ) is the radius of the leading edge (34) at a tip (40) of the fan blade (20) relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R HUB /R TIP ) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25.",
  "title": "Fan blade for a turbofan gas turbine engine"
}