马赫数对超音速涡轮级联曲面上冲击-边界层相互作用的影响

IF 2.2 3区 工程技术 Q2 MECHANICS Theoretical and Computational Fluid Dynamics Pub Date : 2024-07-11 DOI:10.1007/s00162-024-00712-2
Hugo F. S. Lui, William R. Wolf, Tulio R. Ricciardi, Datta V. Gaitonde
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引用次数: 0

摘要

利用壁面分辨大涡模拟研究了超音速涡轮级联的进气马赫数对曲面上冲击-边界层相互作用(SBLI)不稳定性的影响。在基于弦的雷诺数为 395,000 时,考虑了 1.85、2.00 和 2.15 三个进气马赫数。由于进入边界层的状态和局部压力梯度,机翼的弯曲壁对 SBLIs 产生影响。在吸气侧,由于壁面凸起,进入 SBLI 的边界层会在有利的压力梯度和体积膨胀下演变。另一方面,压力侧的凹壁带来了不利的压力梯度和体积压缩。入口马赫数的变化会引起不同的冲击撞击位置,从而增强这些效应。对吸气侧边界层的详细分析表明,较高的马赫数会导致较大的形状系数,有利于气泡的分离和增大,而压力侧则相反。时频分析显示,分离流中存在间歇事件,主要发生在吸气侧的低频和压力侧的中频。增加入口马赫数会导致吸气侧间歇事件的时间尺度增加,这与高速条纹穿透气泡的瞬间有关,会导致局部流动重新附着和气泡收缩。瞬时流动可视化显示,机翼两侧和气泡沿线的湍流边界层上出现了流向涡流。这些涡流影响了边界层中大尺度纵向结构的形成,从而影响了分离气泡内部的质量失衡。
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Mach number effects on shock-boundary layer interactions over curved surfaces of supersonic turbine cascades

The effects of inlet Mach number on the unsteadiness of shock-boundary layer interactions (SBLIs) over curved surfaces are investigated for a supersonic turbine cascade using wall-resolved large eddy simulations. Three inlet Mach numbers, 1.85, 2.00, and 2.15 are considered at a chord-based Reynolds number 395,000. The curved walls of the airfoils impact the SBLIs due to the state of the incoming boundary layers and local pressure gradients. On the suction side, due to the convex wall, the boundary layer entering the SBLI evolves under a favorable pressure gradient and bulk dilatation. On the other hand, the concave wall on the pressure side imposes an adverse pressure gradient and bulk compression. Variations in the inlet Mach number induce different shock impingement locations, enhancing these effects. A detailed characterization of the suction side boundary layers indicates that a higher Mach number leads to larger shape factors, favoring separation and larger bubbles, while the reverse holds for the pressure side. A time-frequency analysis reveals the presence of intermittent events in the separated flow occurring predominantly at low-frequencies on the suction side and at mid-frequencies on the pressure side. Increasing the inlet Mach number leads to an increase in the time scales of the intermittent events on the suction side, which are associated with instants when high-speed streaks penetrate the bubble, causing local flow reattachment and bubble contractions. Instantaneous flow visualizations show the presence of streamwise vortices developing on the turbulent boundary layers on both airfoil sides and along the bubbles. These vortices influence the formation of the large-scale longitudinal structures in the boundary layers, affecting the mass imbalance inside the separation bubbles.

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来源期刊
CiteScore
5.80
自引率
2.90%
发文量
38
审稿时长
>12 weeks
期刊介绍: Theoretical and Computational Fluid Dynamics provides a forum for the cross fertilization of ideas, tools and techniques across all disciplines in which fluid flow plays a role. The focus is on aspects of fluid dynamics where theory and computation are used to provide insights and data upon which solid physical understanding is revealed. We seek research papers, invited review articles, brief communications, letters and comments addressing flow phenomena of relevance to aeronautical, geophysical, environmental, material, mechanical and life sciences. Papers of a purely algorithmic, experimental or engineering application nature, and papers without significant new physical insights, are outside the scope of this journal. For computational work, authors are responsible for ensuring that any artifacts of discretization and/or implementation are sufficiently controlled such that the numerical results unambiguously support the conclusions drawn. Where appropriate, and to the extent possible, such papers should either include or reference supporting documentation in the form of verification and validation studies.
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