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首页> 外文期刊>Acta astronautica >Flow visualization and supersonic combustion studies of an acoustically open strut cavity
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Flow visualization and supersonic combustion studies of an acoustically open strut cavity

机译：声学露天腔的流量可视化和超音速燃烧研究

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In this study, the supersonic flow over strut cavities was experimentally studied to understand flow features. Instantaneous schlieren imaging in non-reacting flow experiments exhibited the seven types of waves associated with cavity pressure oscillations and the formation of unstable shear layers on both sides. The shear layers moved in and out in synchronous and asynchronous modes at the trailing edge of the strut cavities. The symmetrical wave structure appeared on both sides in the synchronous mode, whereas the shear layers appeared in different stages of the cavity pressure oscillation cycle in the asynchronous mode, resulting in an asymmetrical wave structure. The pressure waves generated at the trailing edge of the strut cavities perturbed the shear layers during their movement toward the leading edge, creating a wavy shear layer with alternate troughs and crests. The pressure oscillations of the strut cavities had high-amplitude cavity modes with broadband noises, and their amplitude decreased from the trailing edge to the leading edge. The estimated recovery factor using the time lag between the signals of the leading and trailing edges showed that the flow inside the strut cavities was low subsonic. The measured dominant pressure oscillation modes had a closer match with the Rossiter modes. The pressure coefficient demonstrated that fluid accumulation inside the cavity increased with an increase in the aspect ratio. Furthermore, a higher fluid mass accumulated at the trailing edge than at the leading edge, and the difference in fluid accumulation increased with an increase in the aspect ratio. Supersonic combustion experiments with strut cavities showed that the strut cavity stabilized the flame. Moreover, the addition of an acoustically open strut cavity ahead of the flame-stabilizing cavity advanced the heat release location upstream.
机译：在这项研究中，实验研究了支撑腔的超音速流动以了解流动特征。在非反应流动实验中的瞬时Schlieren成像表现出与腔压力振荡相关的七种类型的波，并且两侧形成不稳定的剪切层。剪切层在支柱腔的后缘处于同步和异步模式中进出。对称波结构在同步模式的两侧出现，而剪切层出现在异步模式下的腔压振荡循环的不同阶段，导致不对称波结构。在支柱腔的后缘处产生的压力波在其朝向前缘的运动期间扰乱了剪切层，形成了具有替代槽和顶部的波浪剪切层。支柱腔的压力振荡具有具有宽带噪声的高幅度腔模式，并且它们的幅度从后缘降低到前缘。使用前沿和后缘信号之间的时间滞后的估计恢复因子表明支柱内腔内的流量低亚音音。测量的主力压力振荡模式与rossiter模式较近匹配。压力系数证明，腔内内的流体积聚随着纵横比的增加而增加。此外，在后缘处积聚的较高的流体质量比在前缘处，并且流体积聚的差异随着纵横比的增加而增加。用支柱腔的超音速燃烧实验表明，支柱腔稳定火焰。此外，在火焰稳定腔之前加入声学的开放支柱腔，在上游的热释放位置提出了热释放位置。

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