GENERATING ELECTRICAL POWER AT HIGH THRUST CONDITIONS

A gas turbine engine (101) for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor (105) and a first electric machine (117) driven by an HP turbine (107), the first electric machine (117) having a first maximum output power; a low-pressure (LP) spool comprising an LP compressor (104) and a second electric machine (119) driven by an LP turbine (108), the second electric machine (119) having a second maximum output power; a combustion system (106) comprising a fuel metering unit; and an engine controller (123) configured to identify a condition to the effect that the engine (101) 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 extracting electrical power from the second electric machine (119) to meet the electrical power demand.