{
  "$type": "site.standard.document",
  "description": "An aircraft system (20) includes a compressor section, a combustor section, a turbine section, an exhaust duct (92) and a flowpath (46). The exhaust duct (92) includes an upstream duct section (96), a plurality of intermediate duct sections (97A,97B) and a downstream duct section (98). A first…",
  "path": "/patents/965089",
  "publishedAt": "2026-05-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D27/10",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "An aircraft system (20) includes a compressor section, a combustor section, a turbine section, an exhaust duct (92) and a flowpath (46). The exhaust duct (92) includes an upstream duct section (96), a plurality of intermediate duct sections (97A,97B) and a downstream duct section (98). A first (97A) of the intermediate duct sections is fluidly discrete from a second (97B) of the intermediate duct sections. The intermediate duct sections (97A,97B) are fluidly coupled in parallel between the upstream duct section (96) and the downstream duct section (98). The flowpath (46) extends sequentially longitudinally through the compressor section, the combustor section, the turbine section, the upstream duct section (96), the intermediate duct sections (97A,97B) and the downstream duct section (98) from an inlet into the flowpath to an outlet (64) from the flowpath.",
  "title": "BIFURCATED EXHAUST DUCT FOR HYBRID AIRCRAFT POWERPLANT"
}