翼身融合运输机分布式电推进系统设计及油耗评估

针对翼身融合运输机开展了分布式电推进系统的总体设计与油耗评估。通过数值计算完成了70t载质量翼身融合飞机的气动设计与优化。在巡航马赫数为0.80和10km高度的设计点,最大升阻比达到了24。通过求解积分边界层方程组,完成了电推进系统的总体设计。电推进系统包含10个推进风扇,风扇直径为1.45m，压比为1.35，巡航功率为2.94MW。建立了考虑燃烧过程的发动机一维性能模型,对发动机油耗进行了评估,获得了不同发动机循环参数下燃油消耗。建模结果表明,基于翼身融合布局和分布式电推进技术,可使运输机的油耗较C-17节省近50%。 

Distributed electrical propulsion system design and fuel consumption evaluation for a blended-wing-body transport

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.