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首页> 外文期刊>Physics of fluids >Identification of the effects of the nozzle-exit boundary-layer thickness and its corresponding Reynolds number in initially highly disturbed subsonic jets
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Identification of the effects of the nozzle-exit boundary-layer thickness and its corresponding Reynolds number in initially highly disturbed subsonic jets

机译:在最初受到高度干扰的亚音速射流中,确定喷嘴出口边界层厚度及其相应的雷诺数的影响

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摘要

The influence of the nozzle-exit boundary-layer thickness in isothermal round jets at a Mach number of 0.9 and at diameter Reynolds numbers ReD ? 5 × 104 is investigated using large-eddy simulations. The originality of this work is that, contrary to previous studies on the topic, the jets are initially highly disturbed, and that the effects of the boundary-layer thickness are explored jointly on the exit turbulence, the shear-layer and jet flow characteristics, and the acoustic field. The jets originate from a pipe of radius r0, and exhibit, at the exit, peak disturbance levels of 9% of the jet velocity, and mean velocity profiles similar to laminar boundary-layer profiles of thickness δ0 = 0.09r0, 0.15r0, 0.25r0, or 0.42r0, yielding 99% velocity thicknesses between 0.07r0 and 0.34r0 and momentum thicknesses δθ(0) between 0.012r0 and 0.05r0. Two sets of computations are reported to distinguish, for the first time to the best of our knowledge, between the effects of the ratio δ0/r0 and of the Reynolds number Reθ based on δθ(0). First, four jets with a fixed diameter, hence at a constant Reynolds number ReD = 5 × 104 giving Reθ = 304, 486, 782, and 1288 depending on δ0, are considered. In this case, due to the increase in Reθ, thickening the initial shear layers mainly results in a weaker mixing-layer development with lower spreading rates and turbulence intensities, and reduced sound levels at all emission angles. Second, four jets at Reynolds numbers ReD between 1.8 × 104 and 8.3 × 104, varying so as to obtain Reθ ? 480 in all simulations, are examined. Here, increasing δ0/r0 has a limited impact on the mixing-layer key features, but clearly leads to a shorter potential core, a more rapid velocity decay, and higher fluctuations on the jet axis, and stronger noise in the downstream direction. Similar trends can be expected for high-Reynolds-number jets in which viscosity plays a negligible role.
机译:在马赫数为0.9且直径为雷诺数ReD的等温圆形喷嘴中,喷嘴出口边界层厚度的影响。使用大涡模拟研究5×104。这项工作的独创性在于,与先前对该主题的研究相反,射流最初受到严重干扰,并且边界层厚度对出口湍流,剪切层和射流特性的共同影响得到了探索,和声场。射流源自半径为r0的管道,并且在出口处表现出射流速度的9%的峰值扰动水平,并且平均速度曲线类似于厚度δ0= 0.09r0、0.15r0、0.25的层状边界层剖面r0或0.42r0,得出0.07r0和0.34r0之间的99%速度厚度以及0.012r0和0.05r0之间的动量厚度δθ(0)。据我们所知,首次进行了两组计算,以区分比率δ0/ r0和基于δθ(0)的雷诺数Reθ的影响。首先,考虑四个具有固定直径的喷嘴,因此,在恒定雷诺数ReD = 5×104的情况下,根据δ0给出Reθ= 304、486、782和1288。在这种情况下,由于Reθ的增加,初始剪切层的加厚主要导致混合层发展较弱,扩散速率和湍流强度较低,并且在所有发射角度的声级均降低。其次,四个雷诺数为ReD的射流在1.8×104和8.3×104之间变化,以获得Reθθ。在所有模拟中均检查480。此处,增加δ0/ r0对混合层关键特征的影响有限,但显然会导致潜在的磁芯更短,速度衰减更快,射流轴上的波动更大以及下游方向上的噪声更大。对于高雷诺数喷嘴,其中粘度起着微不足道的作用,预计会有类似的趋势。

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