{
  "$type": "site.standard.document",
  "description": "A fan blade (100) includes an aerofoil portion (110) including a leading edge (120) extending from a root (140) to a tip (150) and defining a blade span (145) therebetween. A leading edge thickness (TLE) is defined as a thickness of a cross-section at a given radius at a location along a camber…",
  "path": "/patents/1392501",
  "publishedAt": "2024-11-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/141",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A fan blade (100) includes an aerofoil portion (110) including a leading edge (120) extending from a root (140) to a tip (150) and defining a blade span (145) therebetween. A leading edge thickness (TLE) is defined as a thickness of a cross-section at a given radius at a location along a camber line (C) that is 9% of the total length of the camber line (C) from the leading edge (120). For cross-sections through the aerofoil portion (110) at radii between 50% and 70% of the blade span (145) from a root radius, the leading edge thickness (TLE) includes a first maximum value (T1max). For cross-sections through the aerofoil portion (110) at radii greater than 70% of the blade span (145) from the root radius, the leading edge thickness (TLE) includes a second maximum value (T2max) that is between 105% and 125% of the first maximum value (T1max).",
  "title": "FAN BLADE FOR A GAS TURBINE ENGINE"
}