分布式电推进系统飞/发一体化性能分析
Aircraft-engine integrated performance analysis of turbo-electric distributed propulsion
王笑晨 1陈玉春 1贾琳渊2
作者信息
- 1. 西北工业大学动力与能源学院,西安 710072
- 2. 西北工业大学动力与能源学院,西安 710072;中国航发沈阳发动机研究所,沈阳 110015
- 折叠
摘要
为探究涡轮-电分布式推进(turbo-electric distributed propulsion,TeDP)系统的性能方案对飞机任务油耗的影响,建立了推进系统的性能模型和飞/发一体化评估模型.以150座商用客机为例,研究了推进系统设计参数对飞机质量、油耗的影响,并分析了不同电池放电策略能够带来的收益和负面影响.结果表明:燃气涡轮发动机的涡轮前温度和电力系统的相对额定功率均存在使任务油耗最低的最优值;电池的能量应优先用于在负载端无法满载工作时提供功率补充,该放电策略在电池能量密度超过400 Wh/kg时就能实现任务油耗的降低.本文建立的飞/发一体化设计方法可为涡轮-电分布式推进系统的综合优化设计提供参考.
Abstract
In order to explore the influence of the design parameters of the turbo-electric distributed propulsion(TeDP)system on mission fuel consumption,a performance model of the propulsion system and an integrated aircraft-engine evaluation model were established.The influences of the design parameters of the propulsion system on the weight and fuel consumption of the aircraft were studied based on a 150-seats civil aircraft concept.In addition,various operating strategies of battery were analyzed.The results showed that:there existed optimal values of turbine inlet temperature and relative power of electric system to achieve a minimum fuel consumption in mission profile;the energy use of battery should be prioritized to provide power supplementation when the load can't working at full power,which can achieve the reduction of fuel consumption using a battery with energy density higher than 400 W·h/kg.The integrated design method established can provide supports for the optimization design of the TeDP.
关键词
分布式推进/混合动力/飞/发一体化/油耗评估/性能分析Key words
distributed propulsion/hybrid propulsion/aircraft-engine integration/fuel consumption evaluation/performance analysis引用本文复制引用
基金项目
航空发动机及燃气轮机重大专项基础研究项目(J2019-I-0010-0010)
出版年
2024
NETL
NSTL
万方数据