GAS TURBINE ENGINE WITH ALTERNATING PATTERNS OF ACTIVE BURNERS AND METHOD OF CONTROLLING A GAS TURBINE ENGINE

A gas turbine engine includes: a combustor assembly (7) with a plurality of burners (18) circumferentially arranged about an axis (A); a fuel supply system (9), supplying a fuel flowrate (M2) to the burners (18); and a control unit (10), configured to control the fuel flowrate (M2). An equal number...

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Bibliographische Detailangaben
Hauptverfasser:	RINN, Joerg, STUDERUS, Adrien, KELLERER, Rudolf, JAKOBY, Ralf, APPEL, Christoph
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes: a combustor assembly (7) with a plurality of burners (18) circumferentially arranged about an axis (A); a fuel supply system (9), supplying a fuel flowrate (M2) to the burners (18); and a control unit (10), configured to control the fuel flowrate (M2). An equal number of adjacent burners (18) is maintained active in a first partial load condition and in a second partial load condition, and at least one of the burners (18) which are active in the first partial load condition is deactivated in the second partial load condition and at least one of the burners (18) which are inactive in the first partial load condition is activated in the second partial load condition.