Transpiration cooling for conformal and recessed apertures in hypersonic flow with a turbulent boundary layer

IF 2.7 3区 工程技术 Q2 ENGINEERING, MECHANICAL
Rowland Penty Geraets, Andrew Hyslop, Sebastien Wylie, Jim Merrifield, Matthew McGilvray
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Abstract

High equilibrium wall temperatures in hypersonic flight necessitate cooling of apertures (windows) used by outward-looking electromagnetic sensors to meet material temperature limits. The use of transpiration cooling to achieve this is investigated experimentally using a flat plate model with a porous ejector in the University of Oxford’s High Density Tunnel with a Mach 6.1 freestream flow and a turbulent boundary layer. A backward-facing step either upstream or downstream of the porous ejector is introduced to represent a flight geometry after an insulating patch or shroud has been removed. Infrared thermography is used to gather spatially resolved measurements of cooling performance on and downstream of the ejector. For the conformal configuration, the cooling performance on the porous ejector itself is lower than predicted by existing correlations, and comparison with a slot cooling correlation suggests lower cooling performance for the same mass flow rate over most aperture-relevant regions considered. However, this comparison is correlation-based and geometry-specific, so should not be generalised from the present work alone. For both direct cooling on the ejector and downstream cooling, there is a significant discrepancy between the current work and previous experiments using a similar model in the same wind tunnel. With a backward-facing step upstream of the ejector, the coolant fills the separation region, producing a region with high cooling performance, moving the reattachment location downstream, and eliminating the peak in heating at the reattachment point. However, the effectiveness downstream of the reattachment is lower than for a conformal geometry due to increased mixing and lateral spread of coolant. With a backward-facing step downstream of the ejector, the cooling performance is either better than or similar to the conformal case, except for a local overshoot of around 10% near the reattachment point.

具有湍流边界层的高超声速共形孔和凹孔的蒸腾冷却
高超声速飞行的高平衡壁温度需要冷却外视电磁传感器使用的孔径(窗口)以满足材料温度限制。在牛津大学高密度隧道中,利用一个带有多孔喷射器的平板模型,在马赫6.1的自由流和湍流边界层中实验研究了利用蒸发冷却来实现这一目标。在多孔喷射器的上游或下游引入一个向后的步骤,以表示在绝缘贴片或护罩被移除后的飞行几何形状。红外热像仪用于收集喷射器上和下游冷却性能的空间分辨测量。对于保形结构,多孔喷射器本身的冷却性能低于现有相关性的预测,并且与狭缝冷却相关性的比较表明,在考虑的大多数与孔相关的区域,相同质量流量的冷却性能较低。然而,这种比较是基于相关性和几何特定的,所以不应该从目前的工作中单独推广。对于喷射器的直接冷却和下游冷却,目前的工作与以前在同一风洞中使用类似模型的实验存在显著差异。通过喷射器上游的后向台阶,冷却剂填充分离区域,产生一个具有高冷却性能的区域,将再附着位置向下游移动,并消除再附着点的加热峰值。然而,由于增加了混合和冷却剂的横向扩散,下游再附着的有效性低于保形几何。在喷射器的下游有一个向后的台阶,除了在再附着点附近有一个大约10%的局部超调外,冷却性能优于或类似于共形情况。
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来源期刊
Experiments in Fluids
Experiments in Fluids 工程技术-工程:机械
CiteScore
5.10
自引率
12.50%
发文量
157
审稿时长
3.8 months
期刊介绍: Experiments in Fluids examines the advancement, extension, and improvement of new techniques of flow measurement. The journal also publishes contributions that employ existing experimental techniques to gain an understanding of the underlying flow physics in the areas of turbulence, aerodynamics, hydrodynamics, convective heat transfer, combustion, turbomachinery, multi-phase flows, and chemical, biological and geological flows. In addition, readers will find papers that report on investigations combining experimental and analytical/numerical approaches.
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