{
  "$type": "site.standard.document",
  "description": "A system is provided for an aircraft propulsion system (10). This system includes an inlet lip (42), a bulkhead (46) and a piccolo tube (48) for a thermal anti-icing system (38). The inlet lip (42) extends circumferentially about an axial centerline (16). The bulkhead (46) extends circumferentially…",
  "path": "/patents/1422135",
  "publishedAt": "2023-05-31T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D15/04",
    "ROHR INC [US]"
  ],
  "textContent": "A system is provided for an aircraft propulsion system (10). This system includes an inlet lip (42), a bulkhead (46) and a piccolo tube (48) for a thermal anti-icing system (38). The inlet lip (42) extends circumferentially about an axial centerline (16). The bulkhead (46) extends circumferentially about the axial centerline (16). The bulkhead (46) is configured with the inlet lip (42) to form a cavity (72) axially between the inlet lip (42) and the bulkhead (46). The piccolo tube (48) extends circumferentially about the axial centerline (16) within the cavity (72). The piccolo tube (48) is configured with an elliptical cross-sectional geometry.",
  "title": "THERMAL ANTI-ICING SYSTEM WITH NON-CIRCULAR PICCOLO TUBE"
}