{
  "$type": "site.standard.document",
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  "description": "There is provided a gas turbine engine (10) comprising a combustor (16) and a fuel management system (500). The fuel management system (500) comprises a fuel supply line (510), a recirculation line (511) and a heat exchanger (540). The fuel supply line (510) is configured to supply fuel to the…",
  "path": "/patents/1397363",
  "publishedAt": "2025-09-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/14",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "There is provided a gas turbine engine (10) comprising a combustor (16) and a fuel management system (500). The fuel management system (500) comprises a fuel supply line (510), a recirculation line (511) and a heat exchanger (540). The fuel supply line (510) is configured to supply fuel to the combustor (16). The recirculation line (511) is configured to recirculate excess fuel from the fuel supply line (510) to an engine-located fuel tank (560) via a fuel cooling device (570). The fuel cooling device (570) is configured to reject heat from the excess fuel in the recirculation line (511). The heat exchanger (540) is configured to reject heat from a thermal load (44) of the gas turbine engine (10) to fuel in the fuel management system (500). The heat exchanger (540) is disposed on the fuel supply line (510) or on the recirculation line (511). The fuel supply line (510) is configured to receive fuel from an external source (41) and from the engine-located fuel tank (560). Also provided is an aircraft (600) comprising the gas turbine engine (10) and an airframe (40) comprising an airframe-located fuel tank (41) which provides the external source (41) for the fuel supply (510).",
  "title": "GAS TURBINE ENGINE"
}