Adistributed electrical propulsion system was preliminarily designed and its fuel consumption was evaluated for a blended-wing-body transport. Aerodynamic design and optimization for this blended-wing-body transport with 70t pay-loads were completed through numerical computations. At the design point of cruise Mach number 0.80 and cruise altitude 10km

the maximum lift-to-drag ratio reached 24. The preliminary design of distributed electrical propulsion system was accomplished by solving integral boundary layer equations. The electrical propulsion system was composed of 10 electrically driven fans with diameter of 1.45m

pressure ratio of 1.35 and cruise power of 2.94MW. An one-dimensional engine performance model considering the burning process was established and the engine fuel consumption was evaluated for different engine cycles. Analysis shows that the blended-wing-body configuration with distributed electrical propulsion can reduce the fuel consumption by 50% as compared with C-17 transport.