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Experimental study on the rocket-ejector system with a throat in the secondary stream

机译：二次流喉部火箭喷射器系统的实验研究

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摘要

This study concentrated on hot-fire tests to demonstrate the flow characteristics that influenced by the throttle of the secondary stream in the rocket-ejector system. The experiment was conducted under the sea level static (SLS) condition. A small rocket used gaseous oxygen / liquid kerosene propellant as a primary stream supply system, and the high-pressure air bottles were employed as the secondary stream supply system. The equivalence ratio of the rocket, the air mass flow rate and the mixing length were varied to study the performance. The results show that there is a mass flow rate mismatch between the air flow entering through the inlet and the mass flow permitted due to aerodynamic choking. If the air mass flow rate through the throat is more, the inlet may unstart. If the air mass flow rate through the throat is less, the total pressure loss of the air due to the pseudo-shock would be caused under the effect of the suction performance. The unsuitable air mass flow rate is detrimental to RBCC engine operation in the ejector mode. With the increasing equivalence ratio of the rocket, the pressurization performance is improved accordingly, but the suction performance is obviously decreased. When the equivalence ratio is more than 1.1, the reacting shear layer would affect the suction performance. (C) 2021 Elsevier Masson SAS. All rights reserved.
机译：该研究集中在热火试验上，以证明由火箭喷射器系统中的次级流的节流影响的流动特性。该实验是在海平面静态（SLS）条件下进行的。小火箭使用的气态氧/液煤油推进剂作为主要流供应系统，并且高压空气瓶被用作二次流供应系统。火箭的等效比变化，以研究性能，使得气体质量流量和混合长度变化。结果表明，在进入通过入口的空气流动之间存在质量流量不匹配，并且由于空气动力学窒息而允许的质量流量。如果空气质量流量通过喉部更多，则入口可以卸载。如果通过喉部的空气质量流量较少，则由于伪震动引起的空气的总压力损失将在抽吸性能的效果下引起。不适合的空气质量流量对喷射器模式下的RBCC发动机操作有害。随着火箭的等效比的增加，加压性能相应地改善，但抽吸性能明显降低。当等效率大于1.1时，反应剪切层会影响抽吸性能。 （c）2021 Elsevier Masson SAS。版权所有。

著录项

  • 来源
    《Aerospace science and technology》 |2021年第6期|106697.1-106697.9|共9页
  • 作者

    Gu Rui; Sun Mingbo; Cai Zun; Chen Jian; Li Peibo; Dong Zeyu; Wang Taiyu; Yao YiZhi; Huang YuHui;

  • 作者单位

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Chinese Acad Mil Sci Natl Innovat Inst Def Technol Beijing 100071 Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Coll Aerosp Sci & Engn Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Rocket-based combined cycle; Ejector mode; Throttling characteristics; Suction;

    机译：基于火箭的组合循环;喷射器模式;节流特性;抽吸;

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