{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "The invention relates to a front part of an engine nacelle of an aircraft propulsion assembly, comprising an air intake lip (1) and a front frame (2) arranged behind the air intake lip (1) and which connects an external part (12) to an internal part (11) of the air intake lip (1). A de-icing duct…",
  "path": "/patents/1427910",
  "publishedAt": "2021-10-06T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64C7/02",
    "AIRBUS OPERATIONS SAS [FR]"
  ],
  "textContent": "The invention relates to a front part of an engine nacelle of an aircraft propulsion assembly, comprising an air intake lip (1) and a front frame (2) arranged behind the air intake lip (1) and which connects an external part (12) to an internal part (11) of the air intake lip (1). A de-icing duct (7) is formed in front of the front frame (2). The front frame (2) is shaped so that the de-icing duct (7) comprises a main cavity (71) and a thermal transition zone (72) formed behind the main cavity (71) between an internal face (13) of the external part (12) of the air intake lip (1) and said front frame (2). The thermal transition zone (72) extends over a longitudinal dimension (D2) greater than its average radial dimension (D1), the front frame forming, with respect to the internal face (13) of the external part (12) of the air intake lip (1), an angle measured longitudinally between -20° and +10° over the majority of the thermal transition zone (72). [0002] The thermal transition zone prevents excessive heating of an external panel (4) connected to the air intake lip, in particular when the external panel (4) is made of composite material.",
  "title": "FORWARD SECTION OF NACELLE OF AN AIRCRAFT PROPULSION ASSEMBLY COMPRISING A THERMAL TRANSITION ZONE"
}