AXIAL FUEL STAGING SYSTEM FOR A GAS TURBINE COMBUSTOR

An axial fuel staging (AFS) system 122 for a gas turbine combustor 104 is provided. The AFS system includes a secondary fuel injector 130, an injector housing 318 surrounding the secondary fuel injector, and a conduit assembly 136 in flow communication with the secondary fuel injector. The conduit a...

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Bibliographische Detailangaben
Hauptverfasser:	CIHLAR, David William, SINGLEY, Marissa Ann, WILLIS, Christopher Paul, REED, Jonathan Glenn
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:	An axial fuel staging (AFS) system 122 for a gas turbine combustor 104 is provided. The AFS system includes a secondary fuel injector 130, an injector housing 318 surrounding the secondary fuel injector, and a conduit assembly 136 in flow communication with the secondary fuel injector. The conduit assembly includes a first conduit 304 for conveying fuel to the secondary fuel injector, and a second conduit 320 circumscribing the first conduit such that a channel 338 is defined between the first conduit and the second conduit. The first conduit and the second conduit terminate within the injector housing.