COMBINATION AIR ASSIST AND PILOT GASEOUS FUEL CIRCUIT

When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end o...

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Bibliographische Detailangaben
Hauptverfasser:	CORR, II ROBERT ANTHONY, TWARDOCHLEB CHRISTOPHER ZDZISLAW
Format:	Patent
Sprache:	eng
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:	When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air. The atomized pilot liquid fuel may then be combusted,