{
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  "description": "Turbine engine systems (200; 300; 400) and aircraft having such systems are described. The turbine engine systems (200; 300; 400) include a combustor (210; 306) arranged along a core flow path of the turbine engine (200; 300; 400), a drive shaft (220; 312) having at least a compressor section (206…",
  "path": "/patents/1409080",
  "publishedAt": "2024-09-18T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/107",
    "RTX CORP [US]"
  ],
  "textContent": "Turbine engine systems (200; 300; 400) and aircraft having such systems are described. The turbine engine systems (200; 300; 400) include a combustor (210; 306) arranged along a core flow path of the turbine engine (200; 300; 400), a drive shaft (220; 312) having at least a compressor section (206, 208; 304) and a turbine section (212, 214; 308) coupled thereto, a cryogenic fuel tank (224; 318; 404) configured to supply a fuel to the combustor (210; 306), and an expansion turbine (234; 326; 412) mechanically coupled to the drive shaft (220; 312), the expansion turbine (234; 326; 412) configured to receive fuel from the cryogenic fuel tank (224; 318; 404) and expand said fuel, wherein expansion of said fuel by the expansion turbine (234; 326; 412) drives rotation of the expansion turbine (234; 326; 412) to provide power input to the drive shaft (220; 312).",
  "title": "GAS TURBINE ENGINES HAVING CRYOGENIC FUEL SYSTEMS"
}