{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (400) includes a compressor section, a combustor section, a turbine section, a nozzle section, and the compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. The gas turbine engine…",
  "path": "/patents/1419829",
  "publishedAt": "2023-12-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01K25/103",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (400) includes a compressor section, a combustor section, a turbine section, a nozzle section, and the compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. The gas turbine engine further includes a waste heat recovery system (402) including a heat recovery heat exchanger (432) arranged at the nozzle section, wherein the heat recovery heat exchanger (432) is arranged within the nozzle section such that the heat recovery heat exchanger (432) occupies less than an entire area of an exhaust area (548) of the nozzle section and a heat rejection heat exchanger (428) arranged to reduce a temperature of a working fluid of the waste heat recovery system (402).",
  "title": "SUPERCRITICAL CO2 CYCLE FOR GAS TURBINE ENGINES USING PARTIAL CORE EXHAUST FLOW"
}