{
  "$type": "site.standard.document",
  "description": "Gas turbine engines 400; 500; 600 are described. The gas turbine engines 400; 500; 600 includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that…",
  "path": "/patents/1416185",
  "publishedAt": "2024-08-28T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01K23/02",
    "RTX CORP [US]"
  ],
  "textContent": "Gas turbine engines 400; 500; 600 are described. The gas turbine engines 400; 500; 600 includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. A cooling duct 407; 507; 638 is provided that is separate from the core flow path. A waste heat recovery system 402; 502; 602 is arranged with a heat rejection heat exchanger 428; 528; 628 arranged within the cooling duct 407; 507; 638 and a blower 436; 536; 636 is arranged within the cooling duct 407; 507; 638 and configured to generate a pressure drop across the heat rejection heat exchanger 428; 528; 628.",
  "title": "SUPERCRITICAL CO2 CYCLE FOR GAS TURBINE ENGINES USING POWERED COOLING FLOW"
}