Reducing the carbon footprints of aerial transportation became a major target for both industries and academia. Various solutions have been proposed to develop cleaner alternative methods for green transportation. Full electric, hybrid electric, and turboelectric propulsion system architectures intend to reduce greenhouse gas emissions and fuel consumption of today’s aero gas turbine engines. In this study, a turboelectric propulsion system, which is considered as the most promising technology for future aviation is selected for modelling and simulation. As the main power supply, a high fidelity mathematical model of GE T700 turboshaft engine is constructed in MATLAB/Simulink to emulate the technology of today. Selected aero gas turbine’s mathematical model is combined with NASA’s Baseline electrical power distribution architecture which is firstly designed for N-3X turboelectric aircraft. MATLAB/Simulink model is utilized to analyses a single-engine operational scenario of twin-engine aircraft which is a major design consideration due to single-engine failure. Power requirements, distribution percentages, preliminary power assessment for power electronic systems and nominal power capacities of each electrical unit of a turboelectric propulsion system are obtained using GE T700 as the main power supply.

中文翻译：

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使用单涡轮轴发动机运行方案的涡轮电气分布式推进系统的基线架构设计

减少航空运输的碳足迹已成为工业界和学术界的主要目标。已经提出了各种解决方案来开发用于绿色运输的更清洁的替代方法。全电动，混合电动和涡轮电动推进系统架构旨在减少当今航空燃气涡轮发动机的温室气体排放量和燃料消耗。在这项研究中，选择了涡轮电推进系统作为建模和仿真技术，该系统被认为是未来航空业最有希望的技术。作为主要电源，在MATLAB / Simulink中构建了GE T700涡轮轴发动机的高保真数学模型，以模拟当今的技术。选定的航空燃气涡轮机的数学模型与NASA的Baseline配电架构相结合，该架构最初是为N-3X涡轮电动飞机设计的。MATLAB / Simulink模型用于分析双引擎飞机的单引擎操作场景，这是由于单引擎故障而引起的主要设计考虑因素。使用GE T700作为主要电源，可以获得功率需求，配电百分比，功率电子系统的初步功率评估以及涡轮电推进系统每个电气单元的标称功率容量。