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AN EXPERIMENTAL INVESTIGATION OF THE PRESSURE-VELOCITY CROSS-CORRELATION IN AN AXISYMMETRIC JET

机译:轴对称射流压力 - 速度互相关的实验研究

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This study investigates the strength of the pressure-velocity correlations of a Mach 0.6, axisymmetric jet, with an exit nozzle diameter of 50.8mm. Experiments are conducted at a constant exit temperature of 25°C, and exit pressure and temperature are balanced with ambient conditions. The instantaneous velocity measurements are acquired using a multi-component LDA system who 's measurement volume is traversed along several radial and streamwise locations within the potential core, and mixing layer regions of the flow. The fluctuating lip pressure is simultaneously sampled by an azimuthal array of (15) dynamic transducers, evenly spaced at 24°. These are positioned just outside the shear layer near the jet exit at z/D=0.875, and 1.75R from the centerline, where the pressure field has been shown to be hydrodynamic. From this multi-point evaluation, the cross-correlations between the near-field pressure array (fixed), and streamwise component of the velocity field (traversed) are examined as a function of radial, streamwise, and also azimuthal separation. The results illustrate a remarkable coherence between the near field pressure and the velocity field, on the order of 25%. Streamwise convection velocities of 0.77U_j and 0.73U_j are calculated within the potential core and shear layer, respectively. Analysis of the coherency spectra illustrates the fi-equency band of the correlations and suggest that the potential core and mixing layer regions of the flow are, in general, governed by the high and low frequency motions of the flow, respectively. The azimuthal modal distribution of the cross-correlation shows the dominance of the column mode of the jet, with no higher modes exhibited within the potential core region, and only modes 1 & 2 within the shear layer.
机译:本研究研究了马赫0.6,轴对称喷射的压力 - 速度相关的强度,其出口喷嘴直径为50.8mm。实验在25℃的恒定出口温度下进行,并且避开压力和温度与环境条件平衡。使用多组分LDA系统获取瞬时速度测量,该多分量LDA系统沿着潜在核心内的几个径向和流动位置横穿的测量体积和流动的混合层区域。波动唇压通过(15)的动态换能器的方位角阵列同时采样,在24°处均匀地间隔开。这些位于Z / D = 0.875的喷射器出口附近的剪切层外部,并且从中心线的1.75R处于1.75r,其中压力场已经显示为流体动力学。根据该多点评估,将近场压力阵列(固定)和速度场(横逸)的流动分量之间的互相关作为径向,流动,以及方位角分离。结果说明了近场压力和速度场之间的显着相干性,大约为25%。流动向量速度为0.77U_J和0.73U_J,分别在潜在的核心和剪切层内计算。相干光谱的分析说明了相关性的电气衔接带,并表明流动的潜在核心和混合层区域分别由流动的高频率动作控制。互相关的方位形模态分布示出了射流的柱模式的优势,在潜在的核心区域内没有呈现较高的模式,并且仅在剪切层内的模式1和2。

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