SYSTEMS AND METHODS TO MAINTAIN STABILITY OF FUEL FLOW IN GAS TURBINE ENGINES

A system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas turbine. The system also includes a feed compressor disposed along the first fuel line upstream of the ga...

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Bibliographische Detailangaben
Hauptverfasser:	HO HUAN VAN, KELBERT CHRISTOPHER DON, TYREE RONALD FREDERICK, STAMMEN CHRISTOPHER LAVERN
Format:	Patent
Sprache:	eng
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 system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas turbine. The system also includes a feed compressor disposed along the first fuel line upstream of the gas turbine. The feed compressor is configured to pressurize the first fuel provided to the gas turbine. Further, the system includes fuel flow maintenance system configured to provide a pressurized fuel to the first fuel line upstream of the feed compressor in response to an interruption in a flow of the first fuel along the first fuel line to the gas turbine that triggers a transition from the first fuel in the first fuel line to the second fuel in the second fuel line.