GAS TURBINE ENGINE OPERABLE AT VERY LOW PARTIAL LOAD AND METHOD OF CONTROLLING A GAS TURBINE ENGINE

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)...

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Bibliographische Detailangaben
Hauptverfasser:	RINN, Joerg, STUDERUS, Adrien, KELLERER, Rudolf, BURRI, Daniel, JAKOBY, Ralf, APPEL, Christoph
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR 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 HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN WEAPONS
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Beschreibung
Zusammenfassung:	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).