{
  "$type": "site.standard.document",
  "description": "A fuel system (10) for an aircraft comprises a boost pump (22), a main fuel pump (12) and a motive pump (14). The boost pump (22) receives fuel from a storage unit (20). The main fuel pump (12) receives fuel from the boost pump (22) and delivers fuel to a distribution system (16). The motive fuel…",
  "path": "/patents/969333",
  "publishedAt": "2014-10-01T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/10",
    "HAMILTON SUNDSTRAND CORP [US]"
  ],
  "textContent": "A fuel system (10) for an aircraft comprises a boost pump (22), a main fuel pump (12) and a motive pump (14). The boost pump (22) receives fuel from a storage unit (20). The main fuel pump (12) receives fuel from the boost pump (22) and delivers fuel to a distribution system (16). The motive fuel pump (14) receives fuel from the boost pump (22), routes fuel through the storage unit (20), and delivers fuel to an actuator (18A, 18B). A method for delivering fuel in an aircraft comprises pumping fuel from a fuel tank (20) to a distribution system (16) using a main pump (12), pumping fuel from a fuel tank (20) to an actuator using a motive pump (14), and routing fuel from the actuator (18A, 18B) to the main pump (12).",
  "title": "Fuel and actuation system for gas turbine engine and a corresponding method."
}