高背压条件下的超音速混合压缩进气口特性分析

IF 1.7 4区 工程技术 Q3 MECHANICS Shock Waves Pub Date : 2024-07-21 DOI:10.1007/s00193-024-01192-3
N. Khobragade, J. Gustavsson, R. Kumar
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引用次数: 0

摘要

超音速进气道中的背压上升会影响发动机性能,在极端条件下会导致灾难性的非启动现象。本研究使用快速反应压敏涂料,比较了混合压缩进气口在马赫数 3 下未启动时出现的不同背压状态,重点是隔离器流动。在低背压下,隔离器的动态与外部压缩角周围的不稳定性密切相关。在高背压条件下,正常的冲击系决定了从其前导冲击脚向下游的隔振器流场。在非起动开始时,会出现一个斜向冲击系,其中包括大规模的流场分离、边界层增厚以及隔离器底部的不稳定性减弱。与之前的研究一样,在高背压条件下,低频不稳定性和上游波的传播更为显著。然而,本研究还显示,在窄频段内,背压通过声学机制向上游传播,最终导致进气道非启动。非启动开始时,突出频率沿隔离器长度线性变化,与半波谐振器模型非常吻合。抑制首选频率的振荡可能是减轻或延迟进气道非启动的一种有效控制策略。当进气道未启动时,入口处会出现三维分叉冲击,低频时不稳定流会围绕侧壁上的斜冲击溢出。
本文章由计算机程序翻译,如有差异,请以英文原文为准。

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Characterization of a supersonic mixed-compression air intake at high back pressures

The back pressure rise in a supersonic air intake could affect the engine performance and, in extreme conditions, result in a catastrophic unstart phenomenon. The present study compares different back pressure states that occur during an unstart of a mixed-compression air intake at Mach 3 using a fast-response pressure-sensitive paint, with an emphasis on the isolator flow. At low back pressure, the isolator dynamics is strongly correlated with the unsteadiness around the external compression corner. At high back pressure, a normal shock train dictates the isolator flowfield from its leading shock foot downstream. At the onset of unstart, an oblique shock train transpires involving large-scale flow separation, boundary layer thickening, and mitigated unsteadiness at the isolator floor. Like in previous studies, the prominence of low-frequency unsteadiness and upstream wave propagation is observed at high back pressure. However, in addition, the present study shows strong upstream communication of back pressure in a narrow frequency band through acoustic mechanisms, that eventually leads to the intake unstart. At the onset of unstart, the prominent frequency varies linearly along the isolator length, matching closely with the half-wave resonator model. Suppressing the oscillations at the preferred frequencies could be a promising control strategy to mitigate or delay intake unstart. When the intake unstarts, a 3D bifurcated shock stands at the inlet and the unsteady flow spillage takes place around oblique shocks off the sidewalls at low frequencies.

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来源期刊
Shock Waves
Shock Waves 物理-力学
CiteScore
4.10
自引率
9.10%
发文量
41
审稿时长
17.4 months
期刊介绍: Shock Waves provides a forum for presenting and discussing new results in all fields where shock and detonation phenomena play a role. The journal addresses physicists, engineers and applied mathematicians working on theoretical, experimental or numerical issues, including diagnostics and flow visualization. The research fields considered include, but are not limited to, aero- and gas dynamics, acoustics, physical chemistry, condensed matter and plasmas, with applications encompassing materials sciences, space sciences, geosciences, life sciences and medicine. Of particular interest are contributions which provide insights into fundamental aspects of the techniques that are relevant to more than one specific research community. The journal publishes scholarly research papers, invited review articles and short notes, as well as comments on papers already published in this journal. Occasionally concise meeting reports of interest to the Shock Waves community are published.
期刊最新文献
An experimental and kinetic modeling study of the autoignition of syngas mixtures behind reflected shock waves Asymmetry of imploding detonations in thin channels Thematic issue on blast exposure research in military training environments Optical measurement of state variables associated with blast wave evolution Influence of fuel inhomogeneity on detonation wave propagation in a rotating detonation combustor
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