DUAL FUEL AIRCRAFT ENGINE CONTROL SYSTEM AND METHOD FOR OPERATING SAME

A dual fuel engine control system 900 is disclosed including a first fuel control system 700 for controlling the flow of a first fuel 11 to an aircraft gas turbine engine 101 and a second fuel control system 800 for controlling the flow of a second fuel 11 to the aircraft gas turbine engine 101. A m...

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Bibliographische Detailangaben
Hauptverfasser:	MORTON, SCOTT CHANDLER, LEIGHTON, DAVID MARK, KAMATH, DEEPAK MANOHAR
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS FEEDING FUEL TO COMBUSTION APPARATUS GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS 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 TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A dual fuel engine control system 900 is disclosed including a first fuel control system 700 for controlling the flow of a first fuel 11 to an aircraft gas turbine engine 101 and a second fuel control system 800 for controlling the flow of a second fuel 11 to the aircraft gas turbine engine 101. A method of operating a dual fuel aircraft engine control system 900 is disclosed comprising the steps of: activating a first fuel control system 700 for controlling the flow of a first fuel 11 to an aircraft gas turbine engine 101; and activating a second fuel control system 800 for controlling the flow of a second fuel 12 to the aircraft gas turbine engine 101.