System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation

A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	Allen, Jonathan Kay, Kazakis, Michael V, Borchert, Bradford David, Slobodyanskiy, Ilya Aleksandrovich, Sidko, Igor Petrovich, Trout, Jesse Edwin
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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