{
  "$type": "site.standard.document",
  "description": "A gas turbine engine includes: a combustor assembly (7), having a plurality of burners (18); a fuel supply system (9), configured to supply a fuel flowrate (M2) to the burners (18) and including a fuel supply line (17) and a main fuel valve (22) between the fuel supply line (17) and the burners…",
  "path": "/patents/1421890",
  "publishedAt": "2024-04-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C6/003",
    "ANSALDO ENERGIA SWITZERLAND AG [CH]"
  ],
  "textContent": "A gas turbine engine includes: a combustor assembly (7), having a plurality of burners (18); a fuel supply system (9), configured to supply a fuel flowrate (M2) to the burners (18) and including a fuel supply line (17) and a main fuel valve (22) between the fuel supply line (17) and the burners (18); and a control unit (10), configured to control the fuel flowrate (M2) using the main fuel valve (22) in a first load range (LR1) from full load to a threshold partial load. The fuel supply system (9) includes an auxiliary fuel valve (23) fluidly coupled between the fuel supply line (17) and at least a group of associated burners (18). The control unit (10) is further configured to control the fuel flowrate (M2) using the auxiliary fuel valve (23) in a second load range (LR2) from the threshold partial load (LTH) to a minimum load (ML).",
  "title": "GAS TURBINE ENGINE OPERABLE AT VERY LOW PARTIAL LOAD AND METHOD OF CONTROLLING A GAS TURBINE ENGINE"
}