{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) includes a plurality of fuel injectors (24, 26; 44, 46, 48; 66, 68, 70, 72; 74, 76, 78, 80, 82, 84, 86, 88) grouped operatively by stages in a multistage combustor (12; 12'; 12\"). A fuel system (30; 30'; 30\") for the gas turbine engine includes at least one fuel metering…",
  "path": "/patents/996762",
  "publishedAt": "2012-10-24T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/228",
    "HAMILTON SUNDSTRAND CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) includes a plurality of fuel injectors (24, 26; 44, 46, 48; 66, 68, 70, 72; 74, 76, 78, 80, 82, 84, 86, 88) grouped operatively by stages in a multistage combustor (12; 12'; 12\"). A fuel system (30; 30'; 30\") for the gas turbine engine includes at least one fuel metering module (42) per stage of the multistage combustor. Each fuel metering module includes a pump (54), a flow meter (56), a pressure sensor (58), a controller (60), and a motor (62), which work together to control fuel output.",
  "title": "Distributed aircraft engine fuel system"
}