{
  "$type": "site.standard.document",
  "description": "A low pressure turbine, in particular for a gas turbine engine, extends along an axis (3), has an annular conduit (6) for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the…",
  "path": "/patents/967219",
  "publishedAt": "2014-11-19T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D1/04",
    "GE AVIO SRL [IT]"
  ],
  "textContent": "A low pressure turbine, in particular for a gas turbine engine, extends along an axis (3), has an annular conduit (6) for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades (25), which define a plurality of spaces (26) between them in circumferential direction; the spaces (26) are split by respective splitters (32) into a radially outer conduit (26a) and into a radially inner conduit (26b); the radial position of the splitters (32) is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit (26b).",
  "title": "Low pressure turbine provided with splitters at the last stator array"
}