狭缝射流冲击泡沫金属强化换热的数值模拟

为了分析泡沫金属在狭缝射流冲击泡沫金属强化换热的作用,在计算流体力学(CFD)的基础上,采用数值模拟的方法,对影响换热的一系列因素做了详细的研究。在模型中泡沫金属材质为纯铜,尺寸是定值,通过改变喷嘴内空气速度v、泡沫金属孔隙率φ、喷嘴宽度W与泡沫金属的高度H的比值、喷嘴到泡沫金属上表面的高度C与泡沫金属的高度H的比值,来分析各个因素对热表面换热系数、泡沫金属内温度分布和流线分布等因变量的影响。     

狭缝射流冲击泡沫金属强化换热的数值模拟北大核心

为了分析泡沫金属在狭缝射流冲击泡沫金属强化换热的作用,在计算流体力学(CFD)的基础上,采用数值模拟的方法,对影响换热的一系列因素做了详细的研究。在模型中泡沫金属材质为纯铜,尺寸是定值,通过改变喷嘴内空气速度v、泡沫金属孔隙率φ、喷嘴宽度W与泡沫金属的高度H的比值、喷嘴到泡沫金属上表面的高度C与泡沫金属的高度H的比值,来分析各个因素对热表面换热系数、泡沫金属内温度分布和流线分布等因变量的影响。     

SiO_2纳米流体射流冲击泡沫金属强化传热数值模拟

射流冲击拥有强化传热作用,被广泛应用在各个科技领域,而泡沫金属与纳米流体对强化传热起到有利作用。为分析SiO_2纳米流体射流冲击泡沫金属强化传热作用,在计算流体力学(CFD)基础上,通过数值模拟方法对影响传热的一些因素进行分析,通过改变雷诺数(Re)、纳米流体体积分数(ψ)、泡沫金属孔隙率(φ)和高度(H)来分析不同影响因素对表面传热系数的影响。     

射流冲击泡沫金属流动液膜传热的实验研究

薄液膜蒸发由于其优良的传热特性而被广泛应用于工业领域。在流动液膜上表面覆盖铜质泡沫金属,并耦合空气射流冲击,能够进一步强化传热。多孔泡沫金属提供的毛细驱动力能够有效控制流动液膜的厚度以避免干涸,同时多孔材料特殊的固体骨架构造可以扩大固液、气液传热面积。为了研究射流冲击条件下多孔介质覆盖流动液膜的传热特性,本文通过实验方法,对包括液膜流速Vf、空气射流速度Va、液膜厚度δf和多孔介质孔隙率ε在内的影响因素进行分析,研究并对比这些因素对加热壁面温度Tw、表面传热系数hw以及传热系数提升率的影响。     

冲击/发散冷却气膜冷却效率的实验研究

采用红外热像仪对冲击/发散冷却发散壁绝热壁温进行了测试,研究了气膜冷却效率随吹风比、孔间距、冲击间距、发散孔角度及排列方式的变化规律.研究结果表明,气膜冷却效率随发散孔角度的不同而差异较大;35°发散孔的冷却效率随吹风比的增大而减小,90°发散孔的冷却效率随吹风比的变化因孔阵布置方式的不同而有所差异;冲击间距对90°发散孔的冷却效率影响微弱,对35°发散孔的冷却效率影响较大;吹风比相同,孔间距越小冷却效率越高.     

自耦合射流冲击冷却的数值计算

本文利用动网格技术对两维自耦合射流冲击冷却恒热流壁面进行了数值模拟,腔体底面具有一定的运动规律,每个时间步网格会重新划分。通过对流场和温度场的分析,得出以下结论:自耦合射流是零质量射流,射流的截面速度分布具有自相似性。涡对的平移和破碎影响了温度场的分布,从而冲击靶面温度最低点不是出现在射流驻点区,而是对应于涡对破碎、紊流度最大的位置。     

纳米流体射流冲击冷却技术的实验研究

将高传热性能的Cu-水纳米流体作为换热工质引入射流冲击冷却技术,设计并搭建了射流冲击冷却系统,测试了该系统的换热性能和系统压降,研究了纳米粒子体积份额、入口射流速度以及射流冲击高度对系统换热性能的影响。实验结果表明,在液体中添加纳米粒子、增加射流速度、选取合适的射流冲击高度可以有效提高射流冲击冷却效果,且少量纳米粒子的加入并未引起系统压降的明显变化。     

冲击角对射流强化换热影响的数值研究

本文介绍了一种新型的冲击冷却型冷板,重点研究了冲击角对强化换热效果的影响以及对驻点位置的影响,并运用场协同理论分析了射流过程中强化换热的机理.     

微尺度平面射流冲击的强化传热实验研究

本文以煤油为工质进行了窄缝射流冲击传热实验研究。对射流冲击平板时的局部传热分布做了测定，并发现了局部换热强化现象，这是由于存在壁面射流区边界层流动由层流向湍流的过渡。实验采用宽度为１２５μｍ的窄缝喷嘴，射流出口速度为６～１４ｍ／ｓ，雷诺数Ｒｅ范围６００～１２００。     

一种新型阵列射流冲击冷板的实验研究

本文介绍了一种新型的阵列式射流冷板,通过一系列实验,分析了该射流冷却型冷板的性能,实验结果表明,该冷板在系统最高温升不超过40℃的条件下,冷却能力超过了400 W/cm2,实验还表明该新型冷板具有局部冷却能力高、等温好等特点,特别适用于高可靠性和等温性要求的阵列式局部高热流密度军用电子器件的冷却.     

A PIV study of a supersonic impinging jet

The characteristics of supersonic impinging jets are investigated using Particle Image Velocimetry (PIV). The purpose of the experiments is to understand the jet induced forces on STOVL aircraft while hovering close to the ground. For this purpose, a large diameter circular plate was attached at the nozzle exit. The oscillations of the impinging jet generated due to a feedback loop are captured in the PIV images. The instantaneous velocity field measurements are used to describe flow characteristics of the impinging jet. The important flow features such as oscillating shock waves, slipstream shear layers and large scale structures are captured clearly by the PIV. The presence of large scale structures in the impinging jet induced high entrainment velocity in the near hydrodynamic field, which resulted in lift plate suction pressures. A passive control device is used to interfere with the acoustic waves travelling in the ambient medium to suppress the feedback loop. As a consequence, the large scale vortical structures disappeared completely leading to a corresponding reduction in the entrainment.     

An experimental study of the merging probability of double buoyancy-controlled jet flame

This article presents an experimental investigation on the merging probability of buoyancy-controlled jet flames. Two rectangular jet nozzles with different aspect ratios and heat release rates were studied in the open space. The nozzles of the same area with dimensions of 1.5 × 24, 3 × 12, and 6 × 6 mm were used in this article. It is found that the merging probability increases with the heat release rate and decreases with the space between these two nozzles. A model to predict the merging probability has been developed, which is proportional to a dimensionless parameter linearly within a certain scope.     

An experimental study of jet noise part I: Turbulent mixing noise

The characteristics, both spectral and directivity, of turbulent mixing noise in the far field from subsonic and fully-expanded supersonic jet flows have been studied experimentally over an extensive envelope of jet operating conditions (jet exit velocity and temperature). The measurements were conducted in an anechoic room which provides a free-field environment. The results are presented in a systematic manner, and the observed trends and dependencies are discussed in detail. In particular, the changes in detailed jet noise features with varying velocity and exhaust temperature are assessed independently. Empirical prediction schemes or comparisons with recent theoretical investigations are not attempted here. However, the isothermal jet noise results are compared with those predicted by the freely-convecting quadrupole theories (that is, in the absence of any mean flow shrouding effects). The discrepancies between this model and the measurements, many of which have been recently shown to occur due to the presence of mean velocity and temperature gradients surrounding the sources, are obtained accurately over all jet operating conditions of interest.     

An experimental study of jet noise part II: Shock associated noise

The characteristics of the sound field of shock-containing under-expanded jet flows are studied by measuring the noise from a convergent nozzle operated over an extensive envelope of supercritical jet operating conditions. The measurements were conducted in an anechoic facility. They are complementary to the turbulent mixing noise experiments (described in Part I) for subsonic and fully-expanded (shock-free) supersonic jets. The overall results from shock-containing jets are compared directly with the corresponding results from shock-free jets, and the effects of nozzle pressure ratio and jet exhaust temperature on broadband shock-associated noise are assessed independently. For a supersonic jet, the regimes of jet operating conditions, observer angles, and frequencies over which the sound field is dominated by shock-associated noise are identified. Finally, the spectral results are compared in a preliminary manner with the spectra predicted by an existing theoretical model, and good agreement is obtained in most cases.     

HIRFL-CSR实验环电子冷却装置磁场测量

 在HIRFL-CSR实验环电子冷却装置上采用了独立的高精度螺线管串联产生纵向磁场的设计,获得很高的冷却段磁场平行度。使用霍尔片测量磁场的分布,使用磁针测磁方法测量冷却段磁场的磁轴偏角,并根据测量及计算结果对单个线圈磁轴进行微调。测量及调试结果表明,在施加电流为额定电流的一半时,冷却段磁感应强度为0.078 T,剩余磁场小于2×10^-4 T,磁场不平行度小于1×10^-4,达到了预期的设计目标。     

HIRFL-CSR实验环电子冷却装置磁场测量

在HIRFL-CSR实验环电子冷却装置上采用了独立的高精度螺线管串联产生纵向磁场的设计,获得很高的冷却段磁场平行度。使用霍尔片测量磁场的分布,使用磁针测磁方法测量冷却段磁场的磁轴偏角,并根据测量及计算结果对单个线圈磁轴进行微调。测量及调试结果表明,在施加电流为额定电流的一半时,冷却段磁感应强度为0.078 T,剩余磁场小于2×10-4 T,磁场不平行度小于1×10-4,达到了预期的设计目标。     

射流速度和冲击角度对材料去除特性的分析

射流速度和冲击角度会影响冲击射流的动力特性,对射流抛光的材料去除面型和材料去除量有重要的影响。对冲击射流壁面流场结构进行了分析,建立了工件壁面上的速度、压力与冲击角度、射流出口速度的数学关系。在分析理想平面的基础上,重点分析了射流速度和冲击角度的变化对存在表面瑕疵的工件材料去除量的影响。结果表明:对于理想平面,当冲击角度大约为30°时,可得到理想的高斯型面型分布;对于存在瑕疵的工件表面,在小角度冲击时更有利于材料的去除;工件材料的去除量均随着射流速度的增大而增大。