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Internal flow interaction between three parallel modules within a hypersonic inlet/isolator
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DOI：10.1016/j.ast.2025.111177.png)
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Abstract
En 中文
• The asynchronous throttling of three parallel modules within an inlet/isolator has been experimentally studied under a freestream Mach number of 6.0. This paper uncovers the flow interaction between adjacent channels when a single or double engine fails for multiple parallel engines. • When one of the side channels is choked, the interaction intensity along the lateral direction gradually decreases. The spillage effect line shows a sweep backward trend, and as the AR decreases, the backward sweep angle also gradually decreases. Once the middle channel is choked, it causes interaction in the same synchronization and amplitude to the two side channels, and the effect on both side channels is basically the same. The spillage effect line presents a conical shape. • Under bilateral throttling, transverse pressure gradients divert part of the choked flow into unthrottled channels, while the remainder propagates upstream and discharges through the bleed chamber. Throttling side channels generates higher pressure-rise amplitudes than throttling middle/left channels. • By evaluating four throttling processes with given influencing factors, it was found that the degree of damage, in descending order, is as follows: left channel and right channel throttling→ left channel and middle channel throttling→ one of the side channel throttling→ middle channel throttling. The influence distance of the LC throttling is 20.5% longer than that of the MC throttling, and the influence distance of the bilateral channel throttling is 28.6% longer than the combined throttling of the left and middle channels.
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