Preventing surge

The invention discloses a gas turbine engine for an aircraft, and the gas turbine engine 101 comprises a high-pressure (HP) spool comprising an HP compressor 105 and a first electric machine 117 driven by an HP turbine 107; a low-pressure (LP) spool comprising an LP compressor 104 and a second elect...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	CAROLINE LOUISE TURNER
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	The invention discloses a gas turbine engine for an aircraft, and the gas turbine engine 101 comprises a high-pressure (HP) spool comprising an HP compressor 105 and a first electric machine 117 driven by an HP turbine 107; a low-pressure (LP) spool comprising an LP compressor 104 and a second electric machine 119 driven by an LP turbine 108; a combustor 106; an electrical energy storage unit 305;and an engine controller 123 configured to: in response to receipt of a request for an increased electrical power supply by the engine (dPD) within a requested timeframe (dt), evaluating a current HPcompressor surge margin (dRH/RH) and a current LP compressor surge margin (dRL/RL) based on the operating points thereof; in response to evaluating that one or more of the HP compressor 105 and the LP compressor 104 has insufficient surge margin to facilitate a change of electrical power supply at a requested rate (dPD/dt), meeting the requested electrical power demand using the electrical energystorage unit 305 whilst in