类矩形转圆形内转式进气道流向涡的生成与演化

  • 谌业祺 ,
  • 洪雨婷 ,
  • 闫波 ,
  • 黄琪 ,
  • 李祝飞
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  • 1. 中国科学技术大学
    2. 中国科学技术大学近代力学系

收稿日期: 2025-11-27

  修回日期: 2026-03-11

  网络出版日期: 2026-03-16

基金资助

国家自然科学基金;国家自然科学基金;国家自然科学基金;中国科学院基础与交叉前沿科研先导专项

Formation and evolution of streamwise vortices in a rectangular-like to circular shape transition inward turning inlet

  • CHEN Ye-Qi ,
  • HONG Yu-Ting ,
  • YAN Bo ,
  • HUANG Qi ,
  • LI Zhu-Fei
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Received date: 2025-11-27

  Revised date: 2026-03-11

  Online published: 2026-03-16

摘要

针对类矩形转圆形进气道复杂流动,在来流马赫数6条件下,采用数值模拟结合类层析式平面激光散射试验,研究了进气道内流向涡的生成与演化机制,并基于Liutex涡识别方法探究了尖/钝前缘和有/无抽吸缝对流向涡的影响。结果表明:在尖前缘-有抽吸进气道中,唇口激波依次扫掠唇口板和侧壁边界层,诱导生成两处角涡,这些角涡在喉道下游的隔离段中逐渐融合成强度更大的流向涡。对于钝前缘进气道而言,从后掠钝前缘处产生的有旋气流会在外压缩段的壁面拐角处汇聚形成角涡,并在对称面处汇聚形成大尺度流向涡对;在内压缩段,唇口激波先扫掠角涡处的低能流,然后入射在上游已经形成的流向涡对处,这种复杂激波干扰诱导产生了旋转方向与上游流向涡相反的新流向涡;在喉道下游,角涡没有发生融合,而是与流向涡对共同主导隔离段内的流动。钝前缘-有/无抽吸进气道中的流向涡结构和强度基本一致,表明在内压缩段中设置抽吸缝对钝前缘进气道流场均匀性的影响较小。与尖前缘进气道相比,钝前缘进气道因外压缩段流向涡对的影响,隔离段中流向涡的最大Liutex涡通量减小26.2%,隔离段出口总压恢复系数降低9.0%。在设计和评估进气道性能时,应重视前缘钝化的影响,其流动控制策略需着眼于抑制外压缩段的流向涡对。

本文引用格式

谌业祺 , 洪雨婷 , 闫波 , 黄琪 , 李祝飞 . 类矩形转圆形内转式进气道流向涡的生成与演化[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33151

Abstract

The complex flow field in a rectangular-like to circular shape transition inlet is investigated to reveal the formation and evolution mechanisms of streamwise vortices. Numerical simulations combined with tomography-like planar laser scattering are conducted at a Mach number of 6. The effects of the sharp/blunt leading edges and with/without suction are also investigated based on Liutex vortex identification method. The results show that in the inlet with sharp leading edge and suction, the cowl shock sweeps the boundary layer on the cowl wall and the sidewall, inducing two corner vortices in turn, which gradually merge into a stronger streamwise vortex in the isolator. In the inlet with blunt leading edge and suction, the rotational flow generated from the swept blunt leading edge converges at the corners of the external compression section to form corner vortices, while also converging near the symmetry plane to form a large-scale counterrotating vortex pair. In the internal compression section, the cowl shock first sweeps the low-momentum flow rolled-up by the corner vortex, and then incident on the upstream counterrotating vortex pair, which induces new streamwise vortices with the opposite direction of rotation to that of the upstream vortices. In isolator, the corner vortices and the counterrotating vortex pair dominates the flow without merging. The structure and strength of the streamwise vortices in the inlet with blunt leading edge and with/without suction are basically the same, indicating that the suction in the internal compression section has few effects on the flow field uniformity in the inlet with blunt leading edge. Due to the influence of the counterrotating vortex pair in the external compression section, the inlet with blunt leading edge exhibits a 26.2% decrease in the maximum Liutex vortex flux of the streamwise vortices in the isolator and a 9.0% decrease in the total pressure recovery coefficient on the exit compared to the inlet with sharp leading edge. The effect of the bluntness of the leading edge should be emphasized when designing and evaluating the performance of an inlet. The corresponding flow control strategy should focus on suppressing the counterrotating vortex pairs derived from the external compression section.

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