{
  "$type": "site.standard.document",
  "description": "The nose (122) has guide walls which are provided to extend from a leading edge. A leading edge de-icing channel (140) is provided to extend annularly along the edge. The channel is designed to conduct a fluid. The channel is provided with a wall (142) forming the leading edge. The guide surfaces…",
  "path": "/patents/973812",
  "publishedAt": "2014-06-11T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/02",
    "TECHSPACE AERO SA [BE]"
  ],
  "textContent": "The nose (122) has guide walls which are provided to extend from a leading edge. A leading edge de-icing channel (140) is provided to extend annularly along the edge. The channel is designed to conduct a fluid. The channel is provided with a wall (142) forming the leading edge. The guide surfaces of the primary and secondary flows are attached to the wall. Independent claims are included for the following: (1) a compressor of an axial turbomachine; and (2) a axial turbomachine.",
  "title": "SPLITTER OF AN AXIAL TURBOMACHINE, CORRESPONDING COMPRESSOR AND AXIAL TURBOMACHINE"
}