Performance and operability of an electrically driven propulsor

This manuscript discusses the operation of an electrically driven fan for a hybrid-electric propulsion system BAe-146 aircraft. The thrust requirement is fed into integrated cycle and aerodynamic design tool sizing ducted as one main propulsors, podded under wing replacement turbofan engine. electric motor initiated with torque speed requirements dimensional constraints arising from geometry. are derived by changing pressure ratio hub-to-tip to obtain 2-D space. Surface-mounted permanent magnet designs mapped on operational flexibility investigated through three scenarios. In first scenario, aircraft rate climb changed downsize motor. second rated frequency increase power density in third scenario current same purpose. scenarios provide guidelines reducing weight direct drive application.