BURNER FOR A GAS TURBINE AND METHOD FOR REDUCING THERMO-ACOUSTIC OSCILLATIONS IN A GAS TURBINE

A burner for a gas turbine, has an air passage supplied with compressed air and a fuel passage supplied with fuel gas, each passage has a main outlet opening leading into the combustion chamber of the gas turbine, the air and fuel passages connected fluidically together via a connection duct arrange...

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Bibliographische Detailangaben
Hauptverfasser:	PRADE, BERND, KÖSTLIN, BERTHOLD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING BURNERS COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A burner for a gas turbine, has an air passage supplied with compressed air and a fuel passage supplied with fuel gas, each passage has a main outlet opening leading into the combustion chamber of the gas turbine, the air and fuel passages connected fluidically together via a connection duct arranged upstream of the main outlet openings. The burner is configured such that, when air passage is supplied with compressed air and fuel passage is supplied with fuel gas, a portion of the fuel gas flowing in the fuel passage flows via at least one connection duct into the air passage and, for combustion thereof, is introduced through the main outlet opening of the air passage into the interior of the combustion chamber and a remaining portion of the fuel gas is introduced through the main outlet opening of the fuel passage into the interior of the combustion chamber.