Electric turbine bypass fan and compressor for hybrid propulsion

An electric bypass fan and compressor comprising:

• an inlet guide for guiding input air;
• a multistage bypass fan having an input for receiving guided input air from the inlet guide, the multi-stage bypass fan include a plurality of fan rotors, each fan rotor being rotatable independently of each other fan rotor, each of said fan rotor being driven by a corresponding ring motor arranged on the periphery of the corresponding fan rotor, wherein the multistage bypass fan is operative to provide a first output air flow of higher velocity air flow relative to the guided input air;
• a diffuser portion having an input coupled to the first output airflow of the multistage bypass fan and operative to provide a second output air flow having a velocity higher than the first output airflow;
• a multistage compressor having an input coupled to the diffuser output and configured to receive a portion of the second output air flow, the multi-stage compressor including a plurality of compressor rotor and stator stages, forming a compressor stage, each compressor rotor being rotatable independently of each other compressor rotor, each of said compressor rotor being driven by a corresponding ring motor arranged on the periphery of the corresponding compressor rotor, and wherein a compressor stator is disposed between each compressor rotor wherein the multistage compressor is operative to provide an output of a third output air flow;
• a bypass path coupled to the output of the diffuser and operative to provide a portion of fluid flow around the periphery of the multistage compressor.