HYBRID ELECTRIC PULSED-POWER PROPULSION SYSTEM FOR AIRCRAFT

A propulsion system has a gas turbine engine 12 optimized to operate at a single operating condition corresponding to a maximum continuous power output of the gas turbine engine, an electric motor system 18, 20, 32, 34, an electric machine 14 rotatably attached to the gas turbine engine and electric...

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Bibliographische Detailangaben
Hauptverfasser:	HIMMELMANN, Richard A, PERKINSON, Robert H, TONGUE, Stephen E
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC,OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWERSUPPLY SYSTEMS CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CONTROL OR REGULATION THEREOF CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUTPOWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ELECTRICITY GENERATION SYSTEMS FOR STORING ELECTRIC ENERGY
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Beschreibung
Zusammenfassung:	A propulsion system has a gas turbine engine 12 optimized to operate at a single operating condition corresponding to a maximum continuous power output of the gas turbine engine, an electric motor system 18, 20, 32, 34, an electric machine 14 rotatably attached to the gas turbine engine and electrically connected to the electric motor system, and an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine. A method of operating the propulsion system including operating the gas turbine engine for a first period of time to provide electric power to the electric motor system and to recharge the energy storage system, turning off the gas turbine for a second period of time, and discharging the energy storage system to operate the electric motor system during the second period of time.