The aim of this research project was to investigate the benefits of hybrid-distributed propulsion and boundary layer ingestion applied to an airliner similar in size, range and cruise velocity to an Airbus A320. The power system selected consisted of two under-wing mounted conventional turbofans and an electrically driven boundary layer ingesting fan, located at the rear fuselage. The power required to drive the fan is extracted from both turbofans. The worked carried out and presented in this paper offers a new approach to modelling boundary layer ingestion configurations, consisting of using the sliding mesh method to simulate the rotation of the blades within an airflow. The simulations were performed in two phases. The first stage corresponded to the analysis of an isolated configuration, where fuselage and electric fan were considered to be far away from each other such that there is no aerodynamic interference between the fuselage and the electric fan. During the second phase, the simulations were conducted with the electric fan integrated with the airframe, ingesting the boundary layer around the fuselage. The simulations indicate that ingesting the boundary layer results in remarkable improvements reducing drag and increasing propulsive force, reaffirming the potential of this technology to reduce fuel consumption. However, the results also registered a substantial increment in the pitching, rolling and yawing moments in the integrated configuration with respect to the isolated arrangement. This gain needs to be accounted for during early stages of the design process to maintain the stability and control of the aircraft within acceptable margins.

该研究项目的目的是研究将混合分布的推进和边界层摄入应用于一架大小，航程和巡航速度与空客A320相似的客机的好处。所选的动力系统由两个安装在机翼下方的常规涡轮风扇和一个位于后机身的电动边界层进气风扇组成。驱动风扇所需的功率均来自两个涡轮风扇。本文进行和介绍的工作提供了一种建模边界层摄入结构的新方法，包括使用滑动网格方法来模拟气流中叶片的旋转。模拟分两个阶段进行。第一阶段对应于隔离配置的分析，机身和电风扇被认为彼此远离的地方，从而在机身和电风扇之间没有空气动力干扰。在第二阶段中，模拟是使用与机身集成在一起的电风扇进行的，吸收了机身周围的边界层。仿真表明，摄入边界层可显着改善阻力，减小推进力，从而再次证明了该技术降低燃油消耗的潜力。然而，相对于隔离的布置，结果还记录了在集成构造中的俯仰，侧倾和偏航力矩的显着增加。