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首页> 外文会议>2013 48th International Universities' Power Engineering Conference >A review of Turboelectric Distributed Propulsion technologies for N#x002B;3 aircraft electrical systems
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A review of Turboelectric Distributed Propulsion technologies for N#x002B;3 aircraft electrical systems

机译：N + 3飞机电气系统的涡轮电分布式推进技术综述

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In order to minimise the environmental impact of increased air traffic substantial developments in civil aircraft electrical power systems must occur. NASA have set a target to reduce noise by 71dB, NOx emissions by 80% and fuel consumption by 60% for the N+3 generation of aircraft entering into service sometime between 2030 and 2035 [1]. Turboelectric Distributed Propulsion (TeDP) is expected to enable these goals to be met. NASA's N3-X concept aircraft comprises gas turbine engines which drive electrical generators and a DC network distributes power to an array of fans, which provide thrust. Interconnection and protection technologies will also be included to achieve desired levels of reliability of supply to the propulsion motors. This paper outlines the architecture of a generic TeDP system, explores its benefits, describes technical challenges that will need to be overcome and discusses the technical implications of implementing TeDP with regards to electrical system power density and safety.
机译：为了使增加的空中交通的环境影响最小化，必须在民用飞机电力系统中进行实质性的发展。 NASA设定了一个目标，即在2030年至2035年之间的某个时间投入服务的N + 3代飞机，将噪声降低71dB，NOx排放降低80％，燃油消耗降低60％[1]。涡轮电分布式推进（TeDP）有望实现这些目标。美国国家航空航天局（NASA）的N3-X概念飞机包括驱动发电机的燃气涡轮发动机，并且直流网络将功率分配给提供推力的风扇阵列。互连和保护技术也将被包括在内，以实现期望的推进马达供电可靠性水平。本文概述了通用TeDP系统的体系结构，探讨了其优点，描述了需要克服的技术挑战，并讨论了在电气系统功率密度和安全性方面实施TeDP的技术含义。

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