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Research progress on ejector mode of rocket-based combined-cycle engines

机译：基于火箭组合循环发动机喷射器模式的研究进展

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摘要

The Rocket-based Combined-cycle (RBCC) engine is regarded as one of the most efficient propulsion systems for reusable space transportation vehicles and hypersonic cruise vehicles. It can perform excellently over a very broad range of Mach numbers and flight altitudes through multi-mode operations by effectively integrating the high thrust-to-weight ratio of the rocket engine and the high specific impulse of the airbreathing engine. As one of the most distinctive features and advantages of an RBCC engine, the ejector mode is an important mode for supporting the flight vehicle's rapid acceleration and climb. The engine performance, especially the specific impulse in the ejector mode, plays a vital role in determining the majority of the total fuel consumption, the propulsion efficiency of the entire RBCC engine, and further the whole flight trajectory. Therefore, an excellent performance in the ejector mode sufficiently guarantees the competitiveness and application prospect of an RBCC engine. This paper presents a comprehensive and systematic review of the research progress on the ejector mode of RBCC engines in different countries and different historical periods. In the survey, the summary delivers a progress overview on the ejector mode research, which covers a wealth of landmark experimental and application results on the ejector mode research in different historical periods. On this basis, a number of relevant key technologies regarding the study of the ejector mode are proposed, including efficient ejection, efficient mixing and combustion, widely adjustable rocket, widely applicable variable geometry inletozzle design and control, multi-mode flow passage design, and robust mode transition. Several inherent scientific issues involved in these technologies are refined, such as the dynamic air ejection mechanism, combustion and thermal choke mechanism, and the coupling mechanism between air ejection and thermal choke. Finally, the historical development trend of ejector mode research is clarified, and some recommendations for performance improvement and the key technology breakthrough are provided for future ejector mode research of RBCC engines.
机译：基于火箭的组合循环（RBCC）发动机被认为是可重复使用的空间运输车辆和超音速巡航车辆的最有效推进系统之一。它可以通过有效地整合火箭发动机和空气吹气发动机的高特定脉冲的高速增长比，以极广泛的马赫数和飞行高度进行极大的马赫数和飞行。作为RBCC发动机最独特的特征和优点之一之一，喷射器模式是支持飞行车快速加速和爬升的重要模式。引擎性能，特别是喷射器模式中的特定脉冲，在确定总燃料消耗的大部分，整个RBCC发动机的推进效率以及整个飞行轨迹中起着至关重要的作用。因此，喷射器模式中的出色性能充分保证了RBCC发动机的竞争力和应用前景。本文介绍了对不同国家/地区RBC发动机喷射器模式的研究进展的全面和系统审查。在调查中，摘要提供了关于喷射器模式研究的进展概述，该研究涵盖了在不同历史时期的喷射器模式研究中的大量地标实验和应用结果。在此基础上，提出了许多关于喷射器模式研究的相关关键技术，包括有效的喷射，高效的混合和燃烧，广泛可调的火箭，广泛适用的可变几何入口/喷嘴设计和控制，多模流通道设计，鲁棒模式转换。这些技术中涉及的若干内在的科学问题被精制，例如动态空气喷射机构，燃烧和热扼流机构，以及空气喷射和热扼流圈之间的耦合机构。最后，澄清了喷射器模式研究的历史发展趋势，为未来的RBC动力发动机的未来喷射器模式研究提供了一些绩效改进和关键技术突破的一些建议。

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  • 来源
    《Progress in Aerospace Sciences》 |2019年第5期|30-62|共33页
  • 作者

    Shi Lei; Zhao Guojun; Yang Yiyan; Gao Da; Qin Fei; Wei Xianggeng; He Guoqiang;

  • 作者单位

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

    Northwestern Polytech Univ Sci & Technol Combust Internal Flow & Thermal Struct Lab Xian 710072 Shaanxi Peoples R China;

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  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    RBCC; Ejector mode; Thrust augmentation; Thermal choke; Embedded rocket;

    机译：RBCC;喷射器模式;推力增强;热扼流圈;嵌入式火箭;

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