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Synthetic Inlet Conditions for Inhomogeneous Flows from Filters, Packed Beds, or Sinter Plates 过滤器、填料床或烧结板非均匀流的合成入口条件
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-12-12 DOI: 10.1007/s10494-023-00517-z
Seung-Jin Baik, Fabio J. W. A. Martins, Frank Beyrau, Andreas Kempf

A practical method is presented to generate inflow boundary conditions for the laminar but spatially inhomogeneous flow out of filters, packed beds, or sinter plates. A synthetic velocity field that statistically reproduces the outflow characteristics is created based on digitally filtered random noise by the integral lengthscale of the investigated flow at a low computational cost. The method is tested to reproduce a real flow downstream of a sinter plate, which has its velocity measured using a hot-wire anemometer. Results demonstrate that the present method can efficiently generate synthetic inflow fields.

本文介绍了一种实用方法,用于生成过滤器、填料床或烧结板的层流但空间不均匀流出的流入边界条件。该方法基于数字滤波随机噪声,以较低的计算成本,按所研究流体的整体长度尺度创建了一个能在统计上再现流出特性的合成速度场。通过测试,该方法再现了烧结板下游的真实流动,该流动的速度是通过热线风速计测量的。结果表明,本方法可有效生成合成流入场。
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引用次数: 0
LES Modeling of the DLR Generic Single-Cup Spray Combustor: Validation and the Impact of Combustion Chemistry 德国航天中心通用单杯喷雾燃烧器的 LES 建模:验证和燃烧化学的影响
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-12-11 DOI: 10.1007/s10494-023-00512-4
Arvid Åkerblom, Christer Fureby

Turbulent spray combustion in a generic kerosene-fueled single-cup combustor at typical idle and cruise conditions of an aeroengine are studied with Large Eddy Simulations (LES) using Lagrangian spray and finite-rate chemistry combustion modeling. Three reaction mechanisms of varying complexity are used to model the combustion chemistry. The choice of turbulence-chemistry interaction model is shown to affect the results significantly. The impact of the choice of chemical reaction mechanism and the difference in operating conditions are gauged in terms of time-averaged flow, spray, and combustion characteristics as well as unsteady behavior. Good agreement between LES predictions and experimental results are generally observed but with a notable dependence on the choice of chemical reaction mechanism. The mechanism specifically targeting Jet A displays the best agreement. The choice of reaction mechanism is further demonstrated to influence the flow and thermoacoustics in the combustor, resulting in different thermoacoustic modes dominating. The spray cone is found to be too narrow and thin, an inaccuracy which could be remedied by either making the injection method more empirical or by introducing additional models.

采用拉格朗日喷雾和有限速率化学燃烧模型,通过大涡流模拟(LES)研究了在航空发动机典型怠速和巡航条件下,通用煤油燃料单杯燃烧器中的湍流喷雾燃烧。燃烧化学模型采用了三种不同复杂程度的反应机制。结果表明,湍流-化学相互作用模型的选择会对结果产生重大影响。化学反应机理的选择和工作条件的差异对时间平均流动、喷雾和燃烧特性以及非稳态行为的影响得到了衡量。LES 预测结果与实验结果基本吻合,但与化学反应机理的选择有明显关系。专门针对喷气 A 的机理显示出最佳的一致性。反应机理的选择进一步证明会影响燃烧器中的流动和热声,导致不同的热声模式占主导地位。研究发现喷射锥过于狭窄和稀薄,这种不准确性可以通过使喷射方法更加经验化或引入其他模型来弥补。
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引用次数: 0
Enhancing the Aerodynamic Performance of the Savonius Wind Turbine by Utilizing Quarter Elliptical Supplementary Blades 利用四叶椭圆形辅助叶片提高萨沃尼风力涡轮机的空气动力性能
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-12-07 DOI: 10.1007/s10494-023-00516-0
Mohanad Al-Ghriybah, Abdelmajeed Adam Lagum

The application of wind energy leads to reduced greenhouse gas emissions and dependence on conventional sources of fuels. Nevertheless, traditional Savonius wind energy systems suffer from high negative torque and low efficiency. Therefore, the optimization of the blade shape of the Savonius wind turbine is an effective approach to enhance the use of clean and sustainable wind energy. In this work, selecting supplementary blades with quarter elliptical shapes is proposed to optimize the aerodynamic efficiency of the Savonius rotor by enhancing the amount of captured wind at minimal cost. The turbulence model SST/k–ω is used in ANSYS fluent to numerically simulate the performance of the rotor with supplementary blades. As a function of tip speed ratio (TSR), the torque coefficient (Ct) and power coefficient (Cp) are computed. Furthermore, the total pressure, velocity, and streamlines are estimated and analyzed. The results showed that the supplementary blades have the ability to enhance the output power of the turbine by lowering the negative drag behind the returning blade. Overall, the new configuration enhances the suction vortices and reverses flow, leading to better aerodynamic performance. The maximum Cp for the new configuration is observed at TSR = 0.5 with a value of 0.181 which is 13.1% better than the conventional Savonius turbine.

风能的应用减少了温室气体排放和对传统燃料的依赖。然而,传统的萨沃尼风能系统存在负转矩大、效率低的问题。因此,优化萨沃尼风力涡轮机的叶片形状是提高清洁和可持续风能利用率的有效方法。在这项工作中,建议选择四分之一椭圆形的辅助叶片,以最小的成本提高风的捕获量,从而优化萨沃尼乌斯转子的气动效率。ANSYS fluent 中使用湍流模型 SST/k-ω 对带有辅助叶片的转子的性能进行数值模拟。作为叶尖速度比(TSR)的函数,计算了扭矩系数(Ct)和功率系数(Cp)。此外,还估算和分析了总压力、速度和流线。结果表明,辅助叶片能够通过降低返回叶片后的负阻力来提高涡轮机的输出功率。总体而言,新配置增强了吸气涡流和反向流动,从而实现了更好的气动性能。在 TSR = 0.5 时,观察到新配置的最大 Cp 值为 0.181,比传统的萨沃尼乌斯涡轮机好 13.1%。
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引用次数: 0
A Grid-Induced and Physics-Informed Machine Learning CFD Framework for Turbulent Flows 紊流的网格诱导和物理信息机器学习CFD框架
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-12-04 DOI: 10.1007/s10494-023-00506-2
Chin Yik Lee, Stewart Cant

High fidelity computational fluid dynamics (CFD) is increasingly being used to enable deeper understanding of turbulence or to aid in the design of practical engineering systems. While such CFD approaches can predict complex turbulence phenomena, the computational grid often needs to be sufficiently refined to accurately capture the flow, especially at high Reynolds number. As a result, the computational cost of the CFD can become very high. It therefore becomes impractical to adopt such simulations for parametric investigations. To mitigate this, we propose a framework where coarse grid simulations can be used to predict the fine grid results through machine learning. Coarsening the computational grid increases the grid-induced error and affects the prediction of turbulence. This requires an approach that can generate a data-driven surrogate model capable of predicting the local error distribution and correcting for the turbulence quantities. The proposed framework is tested using a turbulent bluff-body flow in an enclosed duct. We first highlight the flow field differences between the fine grid and coarse grid simulations. We then consider a set of scenarios to investigate the capability of the surrogate model to interpolate and extrapolate outside the training data range. The impact of operating conditions and grid sizes are considered. A Random Forest regression algorithm is used to construct the surrogate model. Two different sets of input features are investigated. The first only takes into account the grid-induced error and local flow properties. The second supplements the first using additional variables that serve to capture and generalise turbulence. The global and localised errors for the predictions are quantified. We show that the second set of input features is better at correcting for the biases due to insufficient resolution and spurious flow behaviour, providing more accurate and consistent predictions. The proposed method has proven to be capable of correcting the coarse-grid results and obtaining reasonable predictions for new, unseen cases. Based on the investigated cases, we found this method maximises the benefit of the available data and shows potential for a good predictive capability.

高保真计算流体动力学(CFD)越来越多地被用于更深入地理解湍流或辅助实际工程系统的设计。虽然这种CFD方法可以预测复杂的湍流现象,但计算网格通常需要足够精细才能准确捕获流动,特别是在高雷诺数时。因此,CFD的计算成本会变得非常高。因此,采用这种模拟进行参数化研究是不切实际的。为了缓解这种情况,我们提出了一个框架,其中粗网格模拟可用于通过机器学习预测细网格结果。计算网格的粗化增加了网格引起的误差,影响了湍流的预测。这需要一种能够生成数据驱动的代理模型的方法,该模型能够预测局部误差分布并校正湍流量。采用封闭管道中的紊流崖体流对所提出的框架进行了测试。我们首先强调细网格和粗网格模拟的流场差异。然后,我们考虑一组场景来研究代理模型在训练数据范围之外进行内插和外推的能力。考虑了运行条件和网格大小的影响。采用随机森林回归算法构建代理模型。研究了两组不同的输入特征。第一种方法只考虑网格引起的误差和局部流动特性。第二种方法是对第一种方法的补充,使用额外的变量来捕捉和概括湍流。对预测的全局和局部误差进行了量化。我们表明,第二组输入特征可以更好地纠正由于分辨率不足和虚假流动行为造成的偏差,从而提供更准确和一致的预测。该方法已被证明能够修正粗网格结果,并对新的未知情况获得合理的预测。根据调查的案例,我们发现该方法可以最大限度地利用现有数据,并显示出良好的预测能力。
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引用次数: 0
The Conjecture of a General Law of the Wall for Classical Turbulence Models, Implying a Structural Limitation 经典湍流模型一般壁面定律的猜想,暗示结构限制
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-30 DOI: 10.1007/s10494-023-00511-5
Philippe Spalart

We call classical a transport model in which each governing equation comprises a production term proportional to velocity gradients and terms such as diffusion and dissipation which are built from the internal quantities of the model and are local. They may depend on the wall-normal coordinate y. We consider the layer along a wall in which the total shear stress is uniform, and y is much smaller than the thickness of the full wall layer. We only use channels and boundary layers, but have seen no evidence that pipe flow is different. The conjectured General Law of the Wall (GLW), in contrast with the classical law for mean velocity (U) only, states that every quantity Q in the model (e.g., dissipation, stresses) is the product of four quantities: powers of the friction velocity ({u}_{tau }) and y which satisfy dimensional analysis; a constant C characteristic of the model; and a function f of the wall distance y in wall units, which closely approaches 1 outside the viscous and buffer layers. This is independent of any flow Reynolds number such as the friction Reynolds number in a channel, once it is large enough, and it rigidly constrains the y-dependence of Q outside the wall region: in particular, all the stresses are on plateaus. In the widely accepted velocity law of the wall, the shear rate dU/dy satisfies such a law with C the inverse of the Karman constant (kappa). We cannot prove the GLW property as a theorem, but we provide extensive arguments to the effect that any Classical equation set allows it, and many numerical results support it. A Structural Limitation any Classical Model would suffer from then arises because the results of experiments (not shown here) and Direct Numerical Simulations contradict the GLW, already for some of the Reynolds stresses in simple flows and all the way to the wall (the conflict between the GLW as predicted by Classical turbulence theory, on which the models are based, and measurements was discussed by Townsend as early as Townsend in J Fluid Mech 11:97–120, 1961). This implies that no modification of a model that remains within the classical type can make it agree closely with this key body of results. This has been tolerated for decades, but the GLW is stated here more precisely than it has been implicitly in the literature, it extends all the way to the wall, and it has theoretical interest. It creates a danger for the developing “data-driven” efforts based on Machine Learning in turbulence modelling, which generally involve all six Reynolds stresses and possibly other quantities such as budget terms.

我们称之为经典输运模型,其中每个控制方程包括一个与速度梯度成比例的生产项和扩散和耗散等项,这些项是由模型的内部量建立的,并且是局部的。它们可能依赖于墙-法向坐标y。我们考虑沿墙的层,其中总剪应力是均匀的,y远小于整个墙层的厚度。我们只使用通道和边界层,但没有证据表明管道流动是不同的。与仅适用于平均速度(U)的经典定律相反,推测的一般壁面定律(GLW)指出,模型中的每个量Q(例如耗散、应力)是四个量的乘积:摩擦速度的幂({u}_{tau })和满足量纲分析的y;模型的常数C特性;以及壁面单位中壁面距离y的函数f,它在粘性和缓冲层外接近于1。一旦足够大,它与通道内的任何流动雷诺数(如摩擦雷诺数)无关,并且它严格限制了壁面区域外Q的y依赖性:特别是,所有应力都在平台上。在被广泛接受的壁面速度定律中,剪切速率dU/dy以C为卡门常数的倒数(kappa)满足该定律。我们不能证明GLW性质是一个定理,但我们提供了广泛的论据,表明任何经典方程集都允许它,并且许多数值结果支持它。任何经典模型都会遇到结构限制,因为实验结果(此处未显示)和直接数值模拟的结果与GLW相矛盾,因为简单流动中的一些雷诺应力一直到壁面(模型所基于的经典湍流理论所预测的GLW与测量之间的冲突早在Townsend在J Fluid Mech 11:97 - 120,1961中就已讨论过)。这意味着对经典类型内的模型的任何修改都不能使其与这个关键结果体紧密一致。这已经被容忍了几十年,但GLW在这里的表述比在文献中隐含的更精确,它一直延伸到墙上,它具有理论意义。这给基于机器学习的湍流建模中的“数据驱动”工作带来了危险,这些工作通常涉及所有六种雷诺兹应力,还可能涉及其他数量,如预算项。
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引用次数: 0
Near-Wall Flow Statistics in High-(Re_{tau }) Drag-Reduced Turbulent Boundary Layers 高$$Re_{tau }$$减阻湍流边界层的近壁流动统计
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-25 DOI: 10.1007/s10494-023-00510-6
Rahul Deshpande, Andrea Zampiron, Dileep Chandran, Alexander J. Smits, Ivan Marusic

Manipulating the organized flow in the near-wall region of a turbulent boundary layer is a direct path to achieving skin-friction drag reduction. However, near-wall flow measurements in high Reynolds number ((Re_{tau })) wall flows can be challenging, due to this region’s small physical size and measurement resolution issues. The present study demonstrates the capability of hot-wire (HW) and stereoscopic particle image velocimetry (PIV) techniques of accurately estimating the trends of near-wall flow statistics in high-(Re_{tau }) drag-reduced turbulent boundary layers. The drag reduction strategy considered involves imposition of streamwise travelling waves of spanwise wall oscillations, well known for attenuating the drag-producing near-wall streaks via unsteady cross-flow straining. A flow phase identification methodology is proposed, based on real-time tracking of the wall-oscillation cycle, to estimate the near-wall phase-based statistics from PIV experiments. This methodology is leveraged to investigate phase-specific orientations of the near-wall flow features, which have been shown in the literature to mimic the characteristics of the shear strain vector, dictating the efficacy of this drag reduction scheme. Reconciliation of the HW and PIV measurements demonstrates that the trends exhibited by higher-order moments of the near-wall streamwise velocity fluctuations, with increasing drag reduction, are representative of the inherent flow physics of the drag-reduced flow. Apart from assisting with the design of high-(Re_{tau }) experiments over drag-reducing devices (riblets, plasma actuators, etc.), the present outcomes also inform high-(Re_{tau }) studies in more general three-dimensional wall flows.

操纵湍流边界层近壁区域的有组织流动是实现表面摩擦阻力减小的直接途径。然而,高雷诺数下的近壁流动测量((Re_{tau }))壁流可能具有挑战性,因为该区域的物理尺寸较小且测量分辨率存在问题。本研究证明了热线(HW)和立体粒子图像测速(PIV)技术能够准确估计高流场近壁流动统计趋势(Re_{tau }) 减阻湍流边界层。考虑的减阻策略包括施加沿展向壁面振荡的顺流行波,众所周知,通过非定常横流应变来衰减产生阻力的近壁面条纹。提出了一种基于壁面振荡周期实时跟踪的流相识别方法,用于估计PIV实验中基于近壁面相位的统计量。该方法被用于研究近壁流动特征的相位特定方向,这些特征已在文献中被证明可以模拟剪切应变矢量的特征,从而表明该减阻方案的有效性。HW和PIV测量结果的协调表明,随着减阻的增加,近壁面流向速度波动的高阶矩所表现出的趋势代表了减阻流动的固有流动物理特性。除了协助设计高-(Re_{tau }) 通过对减阻装置(波纹管、等离子体致动器等)的实验,目前的结果也告知高(Re_{tau }) 研究更一般的三维壁面流动。
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引用次数: 0
Integral Turbulent Length and Time Scales of Higher Order Moments 高阶矩的积分湍流长度和时间尺度
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-16 DOI: 10.1007/s10494-023-00509-z
Markus Klein

Turbulent length and time scales represent a fundamental quantity for analysing and modelling turbulent flows. Although higher order statistical moments have been conveniently used for decades to describe the mean behaviour of turbulent fluid flow, the definition of the integral turbulent scales seems to be limited to the velocity or its fluctuation itself (i.e. the first moment). Higher order moments are characterized by smaller integral scales and a framework is proposed for estimating autocorrelation functions and integral turbulent length or time scales of higher order moments under the assumption that the probability distribution of the velocity field is Gaussian. The new relations are tested for synthetic turbulence as well as for DNS data of a turbulent plane jet at Reynolds number 10000. The present results in particular suggest that the length or time scales of higher order moments can be markedly smaller than those of the turbulent variable itself, which has implications for statistical uncertainty estimates of higher order moments.

湍流长度和时间尺度是分析和模拟湍流的基本量。虽然高阶统计矩几十年来一直被方便地用于描述湍流流动的平均行为,但积分湍流尺度的定义似乎仅限于速度或其波动本身(即第一矩)。高阶矩的积分尺度较小,在速度场概率分布为高斯分布的假设下,提出了一种估计高阶矩的自相关函数和积分湍流长度或时间尺度的框架。本文用合成湍流和雷诺数为10000的湍流飞机的DNS数据对新关系式进行了验证。目前的结果特别表明,高阶矩的长度或时间尺度可以明显小于湍流变量本身的长度或时间尺度,这对高阶矩的统计不确定性估计有影响。
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引用次数: 0
High-Order Finite-Difference Schemes for (Hyper-) Viscous Filtering on Non-Uniform Meshes 非均匀网格上(超)粘性过滤的高阶有限差分方案
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-14 DOI: 10.1007/s10494-023-00503-5
Rodolphe Perrin, Eric Lamballais

In this study, the viscous filtering technique is extended to one-sided and biased finite-difference schemes for non-uniform meshes. The most attractive feature of this technique lies in its numerical stability despite the use of a purely explicit time advancement. This feature is well recovered for non-uniform meshes, making the approach as a simple and efficient alternative to the implicit time integration of the viscous term in the context of direct and large-eddy simulation. The rationale to develop generalized filter schemes is presented. After a validation based on the Burgers solution while using a refined mesh in the shock region, it is shown that a high-order formulation can be used to ensure both molecular and artificial dissipation for performing implicit LES of transitional boundary layer while relaxing drastically the time step constraint.

在本研究中,粘性滤波技术被扩展到非均匀网格的单边和偏置有限差分方案。该技术最吸引人的地方在于其数值稳定性,尽管使用的是纯显式时间推进。这一特点在非均匀网格中得到了很好的恢复,使该方法成为直接模拟和大涡度模拟中粘性项隐式时间积分的一种简单而有效的替代方法。本文介绍了开发通用滤波方案的基本原理。在冲击区域使用细化网格的同时,基于布尔格斯解进行了验证,验证结果表明,在执行过渡边界层的隐式 LES 时,可以使用高阶公式确保分子和人工耗散,同时大幅放宽时间步长限制。
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引用次数: 0
Modeling Closed-Loop Control of Installed Jet Noise Using Ginzburg-Landau Equation 利用金兹堡-朗道方程建立喷气噪声闭环控制模型
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-07 DOI: 10.1007/s10494-023-00508-0
Ugur Karban, Eduardo Martini, Peter Jordan

Installation noise is a dominant source associated with aircraft jet engines. Recent studies show that linear wavepacket models can be employed for prediction of installation noise, which suggests that linear control strategies can also be adopted for mitigation of it. We present here a simple model to test different control approaches and highlight the potential restrictions on a successful noise control in an actual jet. The model contains all the essential elements for a realistic representation of the actual control problem: a stochastic wavepacket is obtained via a linear Ginzburg-Landau model; the effect of the wing trailing edge is accounted for by introducing a semi-infinite half plane near the wavepacket; and the actuation is achieved by placing a dipolar point source at the trailing edge, which models a piezoelectric actuator. An optimal causal resolvent-based control method is compared against the classical wave-cancellation method. The effect of the causality constraint on the control performance is tested by placing the sensor at different positions. We demonstrate that when the sensor is not positioned sufficiently upstream of the trailing edge, which can be the case for the actual control problem due to geometric restrictions, causality reduces the control performance. We also show that this limitation can be moderated using the optimal causal control together with modelling of the forcing.

安装噪声是飞机喷气发动机的主要噪声源。最近的研究表明,线性波包模型可用于预测安装噪声,这表明线性控制策略也可用于缓解安装噪声。我们在此介绍一个简单的模型,用于测试不同的控制方法,并强调在实际喷气式飞机中成功控制噪声的潜在限制。该模型包含了真实反映实际控制问题的所有基本要素:通过线性金兹堡-朗道模型获得随机波包;通过在波包附近引入半无限半平面来考虑机翼后缘的影响;通过在后缘放置一个双极点源(压电致动器模型)来实现致动。基于因果解析的最优控制方法与经典的消波方法进行了比较。通过将传感器置于不同位置,测试了因果关系约束对控制性能的影响。我们证明,当传感器没有被充分放置在后缘的上游时(实际控制问题可能会因几何限制而出现这种情况),因果关系会降低控制性能。我们还证明,利用最优因果控制和强迫建模可以缓和这种限制。
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引用次数: 0
Impact of an Adjacent Surface on a Rectangular Overexpanded Supersonic Jet 邻近表面对矩形超音速喷流的影响
IF 2 3区 工程技术 Q3 MECHANICS Pub Date : 2023-11-06 DOI: 10.1007/s10494-023-00505-3
Romain Gojon, Mihai Mihaescu

Flow and acoustic fields of a rectangular over-expanded supersonic jet interacting with an adjacent parallel plate are investigated using compressible Large Eddy Simulations (LES). The jet exits from a converging diverging rectangular nozzle of aspect ratio 2 with a design Mach number 1.5. Four distances (0 to 3 equivalent diameters) between the plate and the adjacent lip of the rectangular jet in the minor axis plane are studied. The geometry of the nozzle, the positions of the plate, and the exit conditions are identical to the ones of an experimental study. Snapshots and mean velocity fields are presented. Good agreement with the PIV experimental measurements is obtained. Previously, the corresponding free jet has been found to undergo a strong flapping motion in the minor axis plane due to screech. Here, it is shown that the intensity of the screech increases for certain distances from the plate and decreases for others, as compared to the corresponding free jet. Two points space-time cross correlations of the pressure along the jet’s shear-layers show, in two cases, an amplification of the aeroacoustic feedback mechanism leading to screech noise in the jet shear-layer closer to the plate. This amplification is due to acoustic waves impinging on the plate, and generating propagating waves back towards the jet, thus exciting the shear-layer at the screech frequency, around the tenth shock cell. Moreover, when the jet develops as a wall jet on the plate, the screech frequency and its associated flapping motion is canceled but a symmetrical oscillation of the jet at a lower frequency becomes dominant and radiates in the near acoustic field. This oscillation mode, as the ones associated with the screech tones for the other cases studied, can be explained by the use of a vortex sheet model of the ideally expanded equivalent planar jet.

利用可压缩大涡流模拟(LES)研究了矩形过扩张超音速射流与相邻平行板相互作用的流场和声场。射流从长径比为 2 的会聚发散矩形喷嘴喷出,设计马赫数为 1.5。研究了板和矩形喷流的相邻唇口在次轴平面上的四个距离(0 至 3 等效直径)。喷嘴的几何形状、板的位置和出口条件与实验研究的相同。结果显示了快照和平均速度场。结果与 PIV 实验测量结果吻合。在此之前,由于尖啸,相应的自由射流在小轴平面上发生了强烈的拍击运动。这里的研究表明,与相应的自由射流相比,尖啸的强度在距离板的某些距离上会增加,而在其他距离上会减弱。沿射流剪切层的压力的两点时空交叉相关性显示,在两种情况下,气声反馈机制被放大,导致在更靠近板的射流剪切层产生尖啸噪声。这种放大是由于声波撞击到板上,并产生向射流方向的传播波,从而在第 10 个冲击单元附近的尖啸频率上激发剪切层。此外,当射流在板上形成壁面射流时,尖啸频率及其相关的拍击运动会被取消,但射流会以较低的频率对称振荡,并在近声场中辐射。这种振荡模式与其他研究案例中与尖啸音有关的振荡模式一样,可以通过使用理想膨胀等效平面射流的涡片模型来解释。
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引用次数: 0
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