Combustor for a sequential gas turbine having a deflection unit between first and second combustion chambers

The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NOx and CO and high thermal efficiency. Further to the present invention providing a method for operating a combustor for a gas turbine and a combustor for a gas turbine a...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Freitag, Ewald, Doebbeling, Klaus
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:	The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NOx and CO and high thermal efficiency. Further to the present invention providing a method for operating a combustor for a gas turbine and a combustor for a gas turbine are disclosed. The combustor includes a first combustion chamber with a wide operating range, a subsequent deflection unit for deflecting the hot gas flow of the first combustion chamber at least in circumferential direction and components for injecting and mixing additional air and/or fuel, and a sequential combustion chamber with a short residence time, where the temperature of the hot gases reaches its maximum.