{
  "$type": "site.standard.document",
  "description": "The gas turbine axial by-pass flow compressor has at least one high-pressure section with a compressor, combustion chamber and turbine, surrounded by a low-pressure section and made with alternating compression (3) and rectifying (4) stages between concentric outer and inner rings. The outer ring…",
  "path": "/patents/1097474",
  "publishedAt": "2003-03-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/24",
    "TECHSPACE AERO SA [BE]"
  ],
  "textContent": "The gas turbine axial by-pass flow compressor has at least one high-pressure section with a compressor, combustion chamber and turbine, surrounded by a low-pressure section and made with alternating compression (3) and rectifying (4) stages between concentric outer and inner rings. The outer ring acts as a separator between primary and secondary gas flows, and its external wall (11) has at least one self-centering thrust point (12) in contact with the ring fixing flange (13). The thrust point is in the form of a thickened portion of the ring wall which also acts as a reinforcing element.",
  "title": "Turbomachine axial compressor with flow splitting device and assembly method for this device"
}