北京航空航天大学学报 ›› 2006, Vol. 32 ›› Issue (03): 263-266.

• 论文 • 上一篇    下一篇

高超声速涡轮/冲压组合发动机方案

朱大明, 陈敏, 唐海龙, 张津   

  1. 北京航空航天大学 能源与动力工程学院, 北京 100083
  • 收稿日期:2005-06-25 出版日期:2006-03-31 发布日期:2010-09-20
  • 作者简介:朱大明(1981-),男,黑龙江延寿人,博士生, daming zhu@126.com.

"Over-under" concept hypersonic turbo-ramjet combined propulsion system

Zhu Daming, Chen Min, Tang Hailong, Zhang Ji   

  1. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2005-06-25 Online:2006-03-31 Published:2010-09-20

摘要: 为满足高超声速运输机在宽广的工作范围内(Ma=0~5,H=0~30?km)稳定,可靠工作,研究了涡轮/冲压组合动力装置并联方案.完成了涡扇发动机和冲压发动机的总体性能方案设计,2种工作模式转换过程和沿飞行轨迹的组合发动机稳态特性模拟也已接近尾声.建立了适合高超声速飞行的涡扇发动机、冲压发动机可变几何的部件级详细性能计算模型,比较分析了涡扇发动机的加力方案;考虑了进气道/发动机流量匹配对发动机特性的影响;给出了涡轮/冲压模式转换阶段的稳态性能仿真结果.

Abstract: Turbo-ramjet combined propulsion system for a hypersonic transport was examined, which can work steadily and reliably in a wide flying-scope(Ma=0~5,H=0~30?km). The overall performance simulation of turbo engine and ramjet engine was accomplished. The simulation of turbo/ramjet mode transition and the steady performance of the combined cycle engine along the aero track was nearly achieved. The performance simulation model includes variable geometry and variable cycle. The model had been tested by testing data. Based on the models of turbo and ramjet engine for hypersonic flight, the engine with afterburner was analyzed and compared with the one without afterburner. The influence of the flux matching with engine and inlet for the turbo engine on the engine performance was analyzed at the same time. At the end, it is shown that the calculational performance of turbo/ramjet mode transition for an "over-under" concept, turbo-ramjet combined engine.

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