{
  "$type": "site.standard.document",
  "description": "A method for assembling a gas turbine engine includes providing a first fan assembly (12) including a plurality of rotor blades (19) that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly (14) axially aft of the first fan…",
  "path": "/patents/1067702",
  "publishedAt": "2006-05-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D1/24",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "A method for assembling a gas turbine engine includes providing a first fan assembly (12) including a plurality of rotor blades (19) that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly (14) axially aft of the first fan assembly, wherein the second fan assembly includes a plurality of rotor blades that are configured to rotate in a second rotational direction, and coupling a gearbox (102) to the second fan assembly that is configured to rotate the second fan assembly at a second rotational speed that is different than the first rotational speed.",
  "title": "Gas turbine engine with counter rotating blades"
}