高超声速串联式组合动力装置方案  

Hypersonic combined cycle engine concept with tandem layout

作　　者：陈敏[1] 唐海龙[1] 朱大明[1] 朱之丽[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《北京航空航天大学学报》2007年第3期265-268,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为保证高超声速运输机在宽广的飞行包线内（Ma=0—5，H=0—30km）稳定可靠工作，对涡轮／冲压组合动力装置串联方案展开研究．首先建立了经试验数据校核的适于高超声速飞行的组合动力装置部件级变循环详细非线性性能计算模型；在此基础上，利用发动机设计点热力循环分析和非设计点性能分析方法对串联方案的综合特性进行评估，最终给出一种经过优化的串联布局涡扇／冲压组合动力装置总体性能设计方案．研究结果表明，优化方案可有效地缩小组合发动机的结构尺寸与重量，有利于进气道，喷管的调节以及冲压燃烧室燃烧的组织．通过综合调整发动机5个可调几何部位以及涡轮发动机燃油流量和冲压燃烧室燃油流量，可以实现涡扇／冲压模式的平稳转换．Hypersonic turbo/ramjet combined cycle engine concept with the tandem layout was investigated to ensure that the civic aircraft can work reliably under a wide range of flight envelope （ Ma = 0-5, H = 0 - 30 km）. A non-linear combine cycle engine model controlled by multiple variables was developed and verified. Based on it, an optimized scheme was then worked out after comprehensive evaluation on the propulsion system integration via the parametric cycle analysis and performance cycle analysis. This scheme is favorable to the reduction in system dimension and weight, the adjustment of the shared inlet and exhaust nozzle, as well as the stability of the ram combustion. Transient simulation on the turbo/ram mode transition was also conducted. Results show that stable mode transition could be acquired through proper modulation of five variable geometries and the fuel flow.

关 键 词：高超声速 组合动力 涡扇发动机 冲压发动机 系统综合 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]