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Effects of air injection throat width on a non-premixed rotating detonation engine

机译：空气喷射喉宽对非预混旋转爆轰发动机的影响

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摘要

Rotating detonation engines are widely studied because of their compact configurations and high thermal cycle efficiency. For simplification, most of the numerical simulations of rotating detonation engines used premixed reactant mixtures. The rotating detonation waves under non-premixed conditions are not studied enough. The width of air injection throat is an important design parameter for a non-premixed rotating detonation engine. Here, a series of three-dimensional numerical simulations of a non-premixed rotating detonation engine with different air injection throat widths are performed. Cases with three different throat widths of 0.4 mm, 1.0 mm and 2.0 mm are calculated. The transient explicit density-based solver in ANSYS Fluent is used to perform the simulations. Detonation combustion happens in different radial domains for different air injection throat widths. When the air injection throat width is 1.0 mm, there is only one rotating detonation wave in the combustion chamber when the total mass flow rate is 272.3 g/s or 500 g/s. When the total mass flow rate is further increased to 1000 g/s, there are two co-rotating detonation waves in the combustion chamber. While for air injection throat width 0.4 mm, the transition to two-wave mode happens at a smaller total mass flow rate of 500 g/s. When the air injection throat width is too large, the interaction between the injection process and the propagating of rotating detonation wave becomes very strong, and the detonation wave quenches due to the insufficient injected reactants. The engine requires a larger total mass flow rate to sustain the continuous propagation of the rotating detonation wave.
机译：由于其紧凑的配置和高热循环效率，旋转爆炸发动机被广泛研究。为了简化，大多数旋转爆轰发动机的数值模拟使用预混合的反应物混合物。未对未预混合条件下的旋转爆震波不够。空气喷射喉部的宽度是非预混旋转爆轰发动机的重要设计参数。这里，执行具有不同空气喷射喉部宽度的非预混旋转爆炸发动机的一系列三维数值模拟。计算具有0.4mm，1.0mm和2.0mm的三种不同喉部宽度的案例。 ANSYS流畅的瞬态显式基于密度的求解器用于执行模拟。爆炸燃烧发生在不同的空气喷射喉部宽度的不同径向域中。当空气喷射喉部宽度为1.0mm时，当总质量流量为272.3g / s或500 g / s时，燃烧室中只有一个旋转爆轰波。当总质量流量进一步增加到1000g / s时，燃烧室中存在两个共旋转的爆轰波。虽然空气喷射喉部宽度为0.4mm，但过渡到两波模式发生在500g / s的较小总质量流速下。当空气喷射喉部宽度过大时，注射过程与旋转爆轰波的传播之间的相互作用变得非常强烈，并且由于注射反应物不足而导致的爆炸波骤冷。发动机需要更大的总质量流量来维持旋转爆轰波的连续传播。

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  • 来源
    《Acta astronautica》 |2019年第6期|189-198|共10页
  • 作者

    Sun Jian; Zhou Jin; Liu Shijie; Lin Zhiyong; Lin Wei;

  • 作者单位

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

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

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

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

    Space Engn Univ Dept Aerosp Sci & Technol Beijing 101416 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

    Rotating detonation wave; Air injection throat width; Total mass flow rate; Propagation mode;

    机译：旋转爆震波;空气注入喉部宽度;总质量流量;传播模式;

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