A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of:


S=(Maximum Electrical Power Generated=PEM1)/(Maximum Dry Thrust=T)

is in a range of between 2.0 and 10.0.