{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "A hybrid propulsion system (100) includes a gas turbine engine (20) having a low speed spool, a high speed spool (32), and a combustor (56). The low speed spool (30) includes a low pressure compressor (44) and a low pressure turbine (46), and the high speed spool includes a high pressure compressor…",
  "path": "/patents/1432796",
  "publishedAt": "2022-12-28T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D27/10",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A hybrid propulsion system (100) includes a gas turbine engine (20) having a low speed spool, a high speed spool (32), and a combustor (56). The low speed spool (30) includes a low pressure compressor (44) and a low pressure turbine (46), and the high speed spool includes a high pressure compressor (52) and a high pressure turbine (54). The hybrid propulsion system also includes a motor (212B) configured to augment rotational power of the high speed spool, a flow modulation device (226) configured to control a combustor bypass air flow (230) around the combustor (56) to the turbine section (28), and a controller (256). The controller (256) is operable to determine a mode of operation, apply supplemental power to the high speed spool using the motor, modulate the combustor bypass air flow using the flow modulation device, and adjust a fuel-air ratio (410) at the combustor based on modulation of the combustor bypass air flow and the supplemental power applied to the high speed spool.",
  "title": "MODULATED COMBUSTOR BYPASS FOR HYBRID IDLE"
}