{
  "$type": "site.standard.document",
  "description": "Turbine engine systems are described. The turbine engine systems (200; 300; 400) include a combustor (212; 312; 412) arranged along a core flow path (C) of the turbine engine, a cryogenic fuel tank (222; 322; 422) configured to supply a fuel to the combustor, a fuel supply line having a first flow…",
  "path": "/patents/1415904",
  "publishedAt": "2024-05-22T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/22",
    "RTX CORP [US]"
  ],
  "textContent": "Turbine engine systems are described. The turbine engine systems (200; 300; 400) include a combustor (212; 312; 412) arranged along a core flow path (C) of the turbine engine, a cryogenic fuel tank (222; 322; 422) configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line (226; 326; 426) and a second flow supply line (228; 328; 428), the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger (232; 332; 432), and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger (240; 342; 442), and a flow controller (224; 324; 424) arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.",
  "title": "GAS TURBINE ENGINES HAVING CRYOGENIC FUEL SYSTEMS"
}