Generating electrical power at high thrust conditions

A gas turbine engine for an aircraft comprising a high pressure (HP) spool, HP compressor 105, a first electric machine 117 having a first maximum output power and driven by HP turbine 107, low-pressure (LP) spool, a second electric machine 119 having a second maximum output power and driven by LP t...

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Bibliographische Detailangaben
1. Verfasser:	Caroline Louise Turner
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CONVERSION OR DISTRIBUTION OF ELECTRIC POWER DYNAMO-ELECTRIC MACHINES ELECTRICITY ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATION HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine for an aircraft comprising a high pressure (HP) spool, HP compressor 105, a first electric machine 117 having a first maximum output power and driven by HP turbine 107, low-pressure (LP) spool, a second electric machine 119 having a second maximum output power and driven by LP turbine 108, an engine controller 123 configured to identify a condition to the effect that the engine is in a maximum take-off mode of operation or a maximum climb mode of operation, and, in response to an electrical power demand being between zero and the second maximum output power, only extract electrical power from the second electric machine to meet the electrical power demand. Maximum take-off or maximum climb modes may be identified by comparing one or more of the altitude, the Mach number and the power lever angle. Both electric machines may be motor-generators.