Multi-stage multi-plane combustion system for a gas turbine engine

A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end (43) of an annular combustion chamber (39) in two spaced injector planes (3,4). Each of the spaced injector planes includes multiple tangential fuel injectors del...

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Bibliographische Detailangaben
Hauptverfasser:	WILLIS, JEFFREY W, PONT, GUILLERMO, MCKEIRNAN, ROBERT D. JR, TOBY, BENJAMIN E
Format:	Patent
Sprache:	eng ; fre ; ger
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:	A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end (43) of an annular combustion chamber (39) in two spaced injector planes (3,4). Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle (48) extends from the tapered inner liner (46) into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes (53) in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes (51) in the cylindrical outer liner (44) introduces more dilution air downstream from the flow control baffle.