SYSTEMS AND METHODS FOR DETERMINATION OF GAS TURBINE FUEL SPLIT FOR HEAD END TEMPERATURE CONTROL

SYSTEMS AND METHODS FOR DETERMINATION OF GAS TURBINE FUEL SPLIT FOR HEAD END TEMPERATURE CONTROL

A method (200) of controlling an operating temperature of a first combustion zone (115) of a combustor (106) of a rotary machine (100) includes determining a current operating temperature and a target operating temperature of a first combustion zone (115) using a digital simulation. The method (200)...

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Bibliographische Detailangaben
Hauptverfasser: THATCHER, Jonathan Carl, HUEY, John Rogers, LOEVEN II, Robert Joseph
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 method (200) of controlling an operating temperature of a first combustion zone (115) of a combustor (106) of a rotary machine (100) includes determining a current operating temperature and a target operating temperature of a first combustion zone (115) using a digital simulation. The method (200) further includes determining a derivative (408) of the current operating temperature with respect to a current fuel split using the digital simulation. The fuel split apportions a total flow of fuel to the combustor (106) between the first combustion zone (115) and a second combustion zone (117). The method (200) also includes calculating a calculated fuel split (410) that results in a calculated operating temperature approaching the target operating temperature. The method (200) further includes channeling a first flow of fuel to the first combustion zone (115) and a second flow of fuel to the second combustion zone (117).