{
  "$type": "site.standard.document",
  "description": "An aircraft engine system includes a core assembly having at least a burner section and a fuel cell (344) configured to generate electrical power. A cryogenic fuel source (324) is configured to supply a fuel through a fuel supply line (326) to each of the burner section and the fuel cell (344) for…",
  "path": "/patents/1394664",
  "publishedAt": "2026-03-04T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D27/10",
    "RTX CORP [US]"
  ],
  "textContent": "An aircraft engine system includes a core assembly having at least a burner section and a fuel cell (344) configured to generate electrical power. A cryogenic fuel source (324) is configured to supply a fuel through a fuel supply line (326) to each of the burner section and the fuel cell (344) for reaction to generate the electrical power. A system controller (342) is configured to direct fuel to each of the combustor section (310) and the fuel cell (344). The controller determines if an amount of fuel in the fuel supply line (326) is in excess of that necessary for operation of the core assembly and, based on a determination that excess fuel is present, the controller is configured to direct at least a portion of the excess fuel from the fuel supply line (326) to the fuel cell (344) to generate the electrical power.",
  "title": "HYBRID ELECTRIC HYDROGEN ENGINE FOR AIRCRAFT"
}