Design of Distributed Mail-Slot Propulsion System on a Hybrid Wingbody Aircraft

This paper deals with designing a thrust distribution strategy when a Turboelectric Distributed Propulsion (TeDP) system of 16 embedded propulsors is installed on an aerodynamically optimized hybrid wing-body configuration. This HWB previously designed to satisfy conditions of trim, longitudinally static stability and specific cargo space is employed as the baseline configuration for the current study of seeking an optimal propulsion/power system. According to the nature of the entrance flow condition for each distributed propulsion passage in hybrid wing-body aircraft, the ingested boundary layer thickness differs and results in different propulsive reaction. An optimal distribution of thrust and power output is determined by how the system utilizes the propulsive characteristics of each passage. The design space and the number of design variables are selected and described accordingly. An actuator disk model is employed to model thrust generation and shaft power from the propulsor. To carry out the optimization of the propulsion/power system on a computationally expensive CFD model, a Kriging method in conjunction with a Genetic Algorithm (GA) is applied. Throughout the design process, the propulsion performances of the sampled propulsion/power system are analyzed and compared to those of a clean flow engine. Besides the thrust and shaft power, the performance metrics includes mass flow rate, fan pressure ratio, propulsive efficiency, and flow distortion. Minimization of total shaft power from the distributed engine is performed at multiple thrust levels. The benefit of boundary layer ingestion propulsion system is quantified via comparison of thrust equivalent, shaft power and mass flow equivalent clean flow engines with CFD based system design. Nomenclature α = Angle of incidence ρ = Density CD = Drag coefficient CP = Specific heat capacity Ct = Thrust coefficient ṁ = Mass flow rate Sref = Reference area Ts = Static temperature ps = Static pressure A = Area Subscript b = baseline 0 = target ADP = Aerodynamic Design Point DPCP = Distortion index FPR = Fan Pressure Ratio MFR = Mass Flow Rate Nc = Fan shaft speed T = Thrust OGV = Outlet Guide Vane PAI = Propulsion Airframe Integration TeDP = Turboelectric Distributed Propulsion x = Axial direction i = index of slot thruster ∞ = free stream total = summation of I from 1 to 8