摘要
基于超声速民机的飞行任务需求,选取3种构型的自适应循环发动机作为超声速客机的备选动力系统并开展总体性能优化对比。构建总体性能数值仿真模型和数学优化模型,确定设计循环参数选取准则;开展自适应循环发动典型状态点的性能优化对比,分析大功率需求状态和低耗油率需求状态下发动机的性能;基于分析结果,选取优选构型开展基于飞行任务需求的设计循环参数优化。结果表明:模式转换能够显著扩展推力范围并降低耗油率,以构型A为例,亚巡状态下推力范围拓宽约14.14%,耗油率降低约5.75%。构型A在亚巡状态下具有耗油率优势,且起飞推力较高。构型B在超巡状态的节流特性线起始段显示出耗油率优势,且适合高起飞总重的飞行器。构型C在亚巡和超巡状态下均表现出低耗油率,且适合载客量较小的超声速客机。通过优化构型C设计循环参数,可以提升飞机起飞总重3.62%,并在超声速巡航状态下降低耗油率约3%,这将有利于增加载客量和飞行航程。
Based on the flight mission demand of supersonic civil transport,three configurations of adaptive cycle engines were selected as candidate propulsion systems and comparison of overall performance optimization was carried out.Numerical simulation model and mathematical optimization model for overall performance were established.The criteria for selecting design cycle parameters were determined.Performance optimization comparisons of three adaptive cycle engines in typical working conditions were conducted,and the performance of the engine under high power demand and low fuel consumption demand conditions was analyzed.Based on the analysis results,the optimal configuration was selected and the design cycle parameters were optimized based on flight mission demand.The results indicate that mode transition can significantly expand the thrust range and reduce fuel consumption.For instance,in Configuration A,the thrust range is broadened by approximately 14.14%and the fuel consumption is reduced by about 5.75%during subsonic cruise.Configuration A exhibits a fuel consumption advantage during subsonic cruise,and also large take-off thrust.Configuration B shows a fuel consumption advantage at the initial segment of the throttle characteristic curve during supersonic cruise,and is suitable for aircraft with high take-off weights.Configuration C demonstrates low fuel consumption in both subsonic and supersonic cruise,and is suitable for smaller supersonic passenger aircraft.By optimizing the design cycle parameters of Configuration C,the aircraft's take-off weight can be increased by 3.62%,and specific fuel consumption during supersonic cruise can be reduced by approximately 3%,which could be beneficial to passenger capacity and flight range.
作者
徐义皓
郑俊超
张纪元
董学智
谭春青
唐海龙
XU Yihao;ZHENG Junchao;ZHANG Jiyuan;DONG Xuezhi;TAN Chunqing;TANG Hailong(Institute for Aero Engine,Tsinghua University,Beijing 100084,China;Research Institute of Aero-Engine,Beihang University,Beijing 102206,China)
出处
《航空动力学报》
北大核心
2025年第9期31-49,共19页
Journal of Aerospace Power
关键词
超声速客机
自适应循环发动机
总体性能优化对比
优势工作模式
最优节流线
supersonic civil transport
adaptive cycle engine
comparison of overall performance optimization
superiority working mode
optimal throttling line
