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Mixing augmentation mechanism induced by the dual injection concept in shcramjet engines

机译：shcramjet发动机中双喷射概念引起的混合增强机制

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摘要

As one of the key techniques, achieving adequate fuel/air mixing before combustion is a task that must be addressed seriously for shock-induced combustion ramjet (shcramjet) engines. In this paper, dual injectors which have been combined by a front hydrogen jet and a rear air jet with different aspect ratios are placed on the second ramp of a shcramjet inlet to promote mixing process between fuel and hypersonic crossflow. At the same time, dual injectors with pure hydrogen injection and the single hydrogen injection with the same injection area are studied as well for comparison. Flow field properties are investigated numerically based on grid independency analysis and code validation. Obtained results predicted by the three-dimensional Reynolds-average Navier-Stokes (RANS) equations coupled with the two equation SST ( )kappa - omega turbulence model show that the grid scale makes only a slight difference to wall pressure profiles for all cases studied in this article. The dual transverse injection system with a front hydrogen jet and a rear air jet is beneficial for improvement of the mixing efficiency between hydrogen and air. Mixing efficiency in the near field increases with increase of aspect ratio of the air porthole. The air porthole in dual transverse injections would accelerate mixing process when compared with the single injection strategy irrespective of aspect ratio of the air porthole.
机译：作为关键技术之一，在燃烧前实现充分的燃油/空气混合是一项任务，对于冲击感应燃烧冲压发动机（shcramjet）发动机，必须认真解决。在本文中，将具有不同长宽比的前氢射流和后空气射流相结合的双喷油嘴放置在shcramjet入口的第二坡道上，以促进燃料和高超声速横流之间的混合过程。同时，还研究了具有纯氢注入的双喷射器和具有相同注入面积的单氢注入器进行比较。基于网格独立性分析和代码验证，对流场特性进行了数值研究。三维雷诺平均Navier-Stokes（RANS）方程与两个方程SST（）kappa-omega湍流模型相结合所获得的结果表明，在以下情况下研究的所有情况下，网格尺度仅对壁压力曲线产生微小影响。本文。具有前氢气射流和后氢气射流的双横向喷射系统有利于提高氢气和空气之间的混合效率。随着空气舷窗的纵横比的增加，近场中的混合效率增加。与单次喷射策略相比，两次横向喷射中的气孔都会加快混合过程，而与气孔的纵横比无关。

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  • 来源
    《Acta astronautica》 |2019年第3期|1-13|共13页
  • 作者

    Du Zhao-bo; Huang Wei; Yan Li; Chen Zheng; Moradi R.;

  • 作者单位

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

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

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

    Shanghai Electromech Engn Inst, Shanghai 201109, Peoples R China;

    Khazar Univ, Sch Engn & Appl Sci, Dept Chem Engn, Baku, Azerbaijan;

  • 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

    Mixing augmentation; Shcramjet engine; Hypersonic flow; Dual injectors; Mixing efficiency;

    机译：混合增强;Shcramjet发动机;人流量;双喷油器;混合效率;

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