航空学报 > 2020, Vol. 41 Issue (11): 123745-123745   doi: 10.7527/S1000-6893.2020.23745

一种多热力循环组合发动机进气道设计方案

蔡伊雯1, 金志光1, 周建兴2, 周航1   

  1. 1. 南京航空航天大学 能源与动力学院, 南京 210016;
    2. 北京空天技术研究所, 北京 100074
  • 收稿日期:2019-12-20 修回日期:2020-01-02 出版日期:2020-11-15 发布日期:2020-06-12
  • 通讯作者: 金志光 E-mail:nuaa_jzg@nuaa.edu.cn

Design scheme of combined multiple thermodynamic cycle engine inlet

CAI Yiwen1, JIN Zhiguang1, ZHOU Jianxing2, ZHOU Hang1   

  1. 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Beijing Aerospace Technology Institute, Beijing 100074, China
  • Received:2019-12-20 Revised:2020-01-02 Online:2020-11-15 Published:2020-06-12

摘要: 针对马赫数0~6的预冷涡轮+冲压组合多热力循环发动机的宽范围工作要求,提出了一种在马赫数2~6范围内流量系数为1.0的宽范围轴对称进气道变几何调节方案,通过中心锥与分流板的协同平移运动,可在满足涡轮与冲压两通道流量分配要求的同时,实现两通道压缩量的匹配调节。对起始半锥角分别为20°和13°的两种变几何进气道方案开展了设计与对比研究。结果表明:起始半锥角对最终方案设计影响最大,起始半锥角为13°的进气道方案较起始半锥角为20°的方案,冲压通道和涡轮通道在来流马赫数为6时临界总压恢复分别提高了16%和14%,最大迎风面积减小了12.4%,但中心锥和分流板平移调节距离分别增加84%和91%。

关键词: 预冷组合发动机, 高流量捕获, 可调进气道, 轴对称进气道, 高超声速

Abstract: To satisfy the requirement of wide range operations for the pre-cooling turbojet + ramjet combined multiple thermodynamic cycle engine with Mach numbers from 0 to 6, a variable geometry adjustment scheme of an axisymmetric inlet with full flow capture ability within Mach number from 2 to 6 is proposed. The mass flow distribution and compression requirement between the turbojet and ramjet passages can be met simultaneously by moving the center cone and the splitter plate. In this paper, the scheme design and comparative study of two variable geometry inlets with initial half cone angles of 13° and 20° respectively are conducted. The results show that the initial half cone angle affects the design of the final scheme most. The inlet scheme with an initial half cone angle of 13° is advantageous over the one with an initial half cone angle of 20° in that the critical total pressure recovery in ramjet and turbojet channels increase by 16% and 14% respectively when the free stream Mach number is 6, and the maximum windward area decreases by 12.4%. However, the moving distances of the center cone and the splitter are increased by 84% and 91% respectively.

Key words: pre-cooling combined engines, high flow capture, variable geometry inlets, axisymmetric inlets, hypersonic

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