Gas turbine engine combustor with fluidic control of swirlers

A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler as...

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Bibliographische Detailangaben
Hauptverfasser:	ZUPANC, FRANK J, TSENG, RAYMOND R
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING BURNERS 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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly. A flow of compressed is directed into the air inlet of the bistable fluidic amplifier and, based on the control air pressure at the control port, the flow of compressed air supplied to the air inlet is selectively directed to either the first air outlet or the second air outlet.