{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "An inlet (18) of a nacelle (16) for channeling inlet airflow to a fan (28) of a gas turbine engine (12) includes a forward lip (40) and an inner surface (46). The forward lip extends around a centerline axis (20) of the engine and is adapted to accommodate a flow angle (²) of incoming airflow. The…",
  "path": "/patents/1015303",
  "publishedAt": "2011-03-02T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/04",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "An inlet (18) of a nacelle (16) for channeling inlet airflow to a fan (28) of a gas turbine engine (12) includes a forward lip (40) and an inner surface (46). The forward lip extends around a centerline axis (20) of the engine and is adapted to accommodate a flow angle (²) of incoming airflow. The inner surface extends from the forward lip along the centerline axis (20) of the engine to adjacent the fan. The inner surface has a first profile (52) above the centerline axis of the engine and a second profile (54) below the centerline axis of the engine. The first profile and the second profile are adapted to define an inlet centerline axis (56) that extends below the centerline axis of the engine at a face (50) of the fan.",
  "title": "Cambered aero-engine inlet"
}