MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE

A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second...

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Bibliographische Detailangaben
Hauptverfasser:	Li, Hejie, Birmaher, Shai, Benjamin, Michael A
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 gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.