We study the effect of power offtake on a high bypass ratio and a low bypass ratio turbofan, taking the power from either the LP or HP spool. The chapter begins with a proposed definition of the degree of hybridization. This relates the level of power extraction to the power potential in the nozzle(s). On the high bypass ratio turbofan, the power offtake and thrust are not interchangeable, and the fan is sized to match the thrust requirement at a design condition with high power offtake, which is similar to some aircraft concepts for distributed propulsion. For the low bypass ratio turbofan, the thrust available depends on the power offtake, similar to some military aircraft or the more-electric-engine approach. In both cases, the behavior of the components is explored when either thrust or power offtake are varied at both altitude cruise and sea level static conditions.