Operating a combustor of a gas turbine

A method of operating a combustor for a turbine in the premixed mode includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. Each nozzle includes an air swirler and the fuel is injected at axially spaced locations on opp...

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Bibliographische Detailangaben
Hauptverfasser:	MICK, WARREN J, COHEN, MITCHELL R
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING 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 method of operating a combustor for a turbine in the premixed mode includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. Each nozzle includes an air swirler and the fuel is injected at axially spaced locations on opposite sides of the swirler. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and also during the transition. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise and the axial staging of the fuel achieves low emission operation in the premixed mode.