{
  "$type": "site.standard.document",
  "description": "A fan assembly (32) for a gas turbine engine includes a plurality of fan blades (40) coupled together such that the fan blades are arranged in a circumferential row (52) extending around a rotor disk (74), wherein each fan blade includes an airfoil including a first sidewall and a second sidewall…",
  "path": "/patents/1070196",
  "publishedAt": "2006-02-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/022",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "A fan assembly (32) for a gas turbine engine includes a plurality of fan blades (40) coupled together such that the fan blades are arranged in a circumferential row (52) extending around a rotor disk (74), wherein each fan blade includes an airfoil including a first sidewall and a second sidewall connected together at a leading edge (42) and a trailing edge (44) and extends radially between a root (46) and a tip (48). The fan assembly also includes at least one shroud (60) coupled to at least one of the plurality of fan blade tips and extending circumferentially around the rotor disk, and at least one row of rotor blades (90) extending radially outward from the at least one shroud. Each rotor blade includes an airfoil including a first sidewall and a second sidewall connected together at a leading edge (92) and a trailing edge (94).",
  "title": "Fan assembly for a gas turbine"
}