{
  "$type": "site.standard.document",
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  "description": "A gas turbine engine, includes: a first-stage combustor (3) with a plurality of first burner assemblies (17); a second-stage combustor (7) with a plurality of second burner assemblies (30), downstream of the first-stage combustor (3); a fuel supply system (9), configured to supply a respective…",
  "path": "/patents/1409048",
  "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 first-stage combustor (3) with a plurality of first burner assemblies (17); a second-stage combustor (7) with a plurality of second burner assemblies (30), downstream of the first-stage combustor (3); a fuel supply system (9), configured to supply a respective first fuel flowrate (FM1) to each first burner assembly (17) and a respective second fuel flowrate (FM2) to each second burner assembly (30); and a controller (10), configured to control the first fuel flowrate (FM1) and the second fuel flowrate (FM2). The controller (10) is further configured to selectively activate and deactivate the second burner assemblies (30) and to supply a first value of the first fuel flowrate (FM1) to a first group of the first burner assemblies (17) and a second value of the first fuel flowrate (FM1) to a second group of the first burner assemblies (17) in partial load operating condition while at least a first group of the second burner assemblies (30) are inactive, the first value of the first fuel flowrate (FM1) being lower than the second value of the first fuel flowrate (FM1) or being zero flowrate.",
  "title": "GAS TURBINE ENGINE WITH FIRST AND SECOND STAGE FUEL CONTROL AND METHOD OF CONTROLLING A GAS TURBINE ENGINE"
}