GAS TURBINE ENGINE WITH VARIABLE SPEED OUTPUT

A gas turbine engine (10) for an aircraft includes at least a low pressure spool (26) with a low pressure turbine shaft (24) operatively connected to at least one turbine (20), the low pressure turbine shaft (24) rotatable about an engine axis, and a low pressure compressor (12) operatively connected to a low pressure compressor shaft (32) that is independently rotatable relative to the low pressure turbine shaft (24). A differential gearbox (30; 130) has an input operatively connected to the low pressure turbine shaft (24), a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft (32) and the second output of the differential gearbox (30; 130) operatively connected to an output shaft (26) of the gas turbine engine (10). The differential gearbox (30; 130) permits the output shaft (26), the low pressure compressor shaft (32) and the low pressure turbine shaft (24) to rotate at different speeds.