GAS TURBINE FIRING TEMPERATURE OPTIMIZATION BASED ON SULFUR CONTENT OF FUEL SUPPLY

Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic...

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Bibliographische Detailangaben
Hauptverfasser:	CAREY BRADLEY STEVEN, THATCHER ROBERT THOMAS, LOMAS ARIEL HARTER, GLASER PAUL BURCHELL, RODWELL ANDREW MITCHELL
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIRCHEMICAL OR PHYSICAL PROPERTIES LIGHTING MEASURING MECHANICAL ENGINEERING PHYSICS TESTING WEAPONS
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Beschreibung
Zusammenfassung:	Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system.