{
  "$type": "site.standard.document",
  "coverImage": {
    "$type": "blob",
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    "mimeType": "image/png",
    "size": 97022
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  "description": "A gas turbine engine (20) includes a propulsor for providing air into a core engine housing and propulsion air radially outwardly of the core engine housing. The core engine housing surrounds a compressor section. A combustor is positioned downstream of the compressor section and a turbine section…",
  "path": "/patents/1391162",
  "publishedAt": "2026-03-04T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/047",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A gas turbine engine (20) includes a propulsor for providing air into a core engine housing and propulsion air radially outwardly of the core engine housing. The core engine housing surrounds a compressor section. A combustor is positioned downstream of the compressor section and a turbine section is positioned downstream of the combustor. An aircraft fluid moves within an inlet (32) to the gas turbine engine (20), and is exposed to inlet air (C) at the inlet (32). There is a first temperature sensor (56) for sensing a first temperature of the aircraft at a first upstream point and a second temperature sensor (54) for sensing a second temperature of the aircraft fluid at a second downstream point where the aircraft fluid has been exposed to the inlet air (C) for a period of time. A control (100) determines a temperature differential between first and second temperatures sensed by the first and second temperature sensors (56, 54). The temperature differential is associated with a likelihood that an icing condition will occur, and the control (100) is programmed to take a corrective action should an icing condition be identified.",
  "title": "ICING CONDITION IDENTIFICATION FOR GAS TURBINE ENGINE"
}