Reducing idle thrust in a propulsive gas turbine

A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine 110 driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine 110 driven by an LP turbine; and an engine controller 30...

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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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine 110 driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine 110 driven by an LP turbine; and an engine controller 309 configured to identify a condition to the effect that the engine is in an approach idle condition, and operate the first electric machine in a motor mode and operate the second electric machine in a generator mode to transfer power electrically from the LP spool to the HP spool to thereby reduce the LP spool rotational speed and increase the HP spool rotational speed. The engine may further comprise a fan forming part of the low-pressure spool, whereby reduction of the low-pressure spool speed reduces the thrust produced by the engine. There may be a reduction bear box connecting the low-pressure pool to the fan.