{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) includes a first spool (14,16), a second spool (12), a primary combustor (70), and a diffuser (68). The first spool (14,16) includes a first compressor (18,24) rotationally driven by a first turbine (20,26) via a first shaft (22,28). The second spool (12) includes a second…",
  "path": "/patents/1410818",
  "publishedAt": "2024-05-29T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/113",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) includes a first spool (14,16), a second spool (12), a primary combustor (70), and a diffuser (68). The first spool (14,16) includes a first compressor (18,24) rotationally driven by a first turbine (20,26) via a first shaft (22,28). The second spool (12) includes a second compressor (74) driven by a second turbine (76) via a second shaft (78). The first compressor (18,24), the diffuser (68), and the primary combustor (70) are arranged in series to provide a compressed airflow discharged from the first compressor (18,24) to the primary combustor (70) via the diffuser (68), which includes walls that diverge towards the primary combustor (70). The second compressor (74) is fluidly coupled to the diffuser (68) to receive at least a portion of the compressed airflow from the diffuser (68). The second turbine (76) is fluidly coupled to the diffuser (68) to discharge an expanded airflow to the diffuser (68).",
  "title": "ADAPTIVE ENGINE WITH BOOST SPOOL"
}