SYSTEMS AND METHODS FOR HIGH VOLUMETRIC OXIDANT FLOW IN GAS TURBINE ENGINE WITH EXHAUST GAS RECIRCULATION

A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover a...

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Bibliographische Detailangaben
Hauptverfasser:	SLOBODYANSKIY, Ilya Aleksandrovich, TROUT, Jesse Edwin, VALEEV, Almaz, BORCHERT, Bradford David, SIDKO, Igor Petrovich, GINESIN, Leonid Yul'evich, SIMMONS, Scott Robert
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN WEAPONS
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Beschreibung
Zusammenfassung:	A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.