{
  "$type": "site.standard.document",
  "description": "A turbofan engine (20) has an engine case (22) and a gaspath through the engine case (22). A fan (42) has a circumferential array of fan blades (70). The engine further has a compressor, a combustor, a gas generating turbine (26), and a low pressure turbine section (27). A speed reduction mechanism…",
  "path": "/patents/994922",
  "publishedAt": "2012-12-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D1/02",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A turbofan engine (20) has an engine case (22) and a gaspath through the engine case (22). A fan (42) has a circumferential array of fan blades (70). The engine further has a compressor, a combustor, a gas generating turbine (26), and a low pressure turbine section (27). A speed reduction mechanism (46) couples the low pressure turbine section (27) to the fan (42). A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.",
  "title": "Turbine section of high bypass turbofan"
}