Turbulent flow and heat transfer characteristics of a two-dimensional oblique plate impinging jet

Turbulent flow and heat transfer characteristics of a two-dimensional oblique plate impinging jet (OPIJ) were experimentally investigated. The local heat transfer coefficients were measured using thermochromic liquid crystals. The jet mean velocity and turbulent intensity profiles were also measured along the plate. The jet Reynolds number (Re, based on the nozzle width) ranged from 10, 000 to 35,000, the nozzle-to-plate distance (H/B) from 2 to 16, and the oblique angle (α) from 60 to 90 degree. It has been found that the stagnation point shifted toward the minor flow region as the oblique angle decreased and the position of the stagnation point nearly coincided with that of the maximum turbulent intensity. It has also been observed that the local Nusselt numbers in the minor flow region were larger than those in the major flow region for the same distance along the plate mainly due to the higher levels in turbulent intensity caused by more active mixing of the jet flow.     

The effects of the compressibility of the subsonic flow on heat transfer characteristics in a microscale impinging slot jet

We experimentally investigated the effects of both the compressibility and nozzle width on the local heat transfer distribution of microscale unconfmed slot jets impinging on a uniformly heated flat plate. We made heat transfer measurements under the following experimental conditions; Reynolds numbers of Re = 4000~10000, Mach numbers of Ma = 0.13~0.68, nozzle-to-plate distances of H/B = 3~25, lateral distances of x/B = 0~25, and nozzle widths of B = 300~700 μm having a nozzle aspect ratio of y/B = 30. A thermal infrared imaging technique was used to measure the impingement plate temperature. The experimental results show that for all tested Re and H/B values at a nozzle width of B = 300 μm, the Nusselt number maximum occurred nearly at the stagnation point and then monotonically decreased along the downstream. However, at B = 500 and 700 μm, the maximum Nusselt number point shifted toward x/B ≈ 1.5~2.0. And the Nusselt number increased, as x/B increased, from the stagnation point to the shifted maximum point and monotonically decreased afterward. This shifted maximum point may be attributable to vortex rings promoting sudden flow acceleration and entrainment of surrounding air moving along the jet axis. For the same Reynolds number, the Nusselt number in the stagnation region increased as the nozzle width increased due to a momentum increase of the jet flow caused by the formation of vortices. And, the Nusselt numbers for the smallest nozzle width of B = 300 μm (or highest Mach number at a given Reynolds number) at all H/B and Reynolds numbers tested significantly deviated from those for B = 500 and 700 μm in the downstream region corresponding to x/B > 5, suggesting that the compressibility, when it is high, can affect the heat transfer in the downstream region.

     

Jet flow characteristics of sinusoidal wavy nozzles

The flow characteristics of jets issued from a sinusoidal nozzle with in-phase and 180° out-of-phase exit configurations were investigated using PIV (particle image velocimetry) and flow visualization techniques. The experiments were carried out at a Reynolds number of about 6300 based on the mean width of the jet nozzle. Compared to a normal rectangular jet, the sinusoidal nozzle jets have smaller velocity deficits as the flow goes downstream. In addition, the turbulence intensity is suppressed in the horizontal center plane. For the case of in-phase wavy nozzle jet, the length of the potential core exhibits small variations along the lateral direction, while the 180° out-of-phase wavy nozzle jet shows large lateral variation in the length of potential core. The turbulent kinetic energy of the 180° out-ofphase nozzle jet also shows sinusoidal variation in the horizontal planes. Large-scale vortices shed from the sinusoidal edge of the nozzle interact strongly and migrate toward the center plane as the flow develops downstream.     

A suggestion of a new method for the calculation of the coating thickness in continuous hot-dip galvanizing

It is known that the distributions of the impinging pressure gradient and the shear stress at the strip surface play a decisive key role in the decision of the coating thickness in hot-dip galvanizing. So, to predict the exact coating thickness, it is essential that the distributions of the impinging wall jet pressure and the shear stress acting between the liquid film and jet stream are measured (or calculated) exactly for each specific coating condition. So far, to obtain the impinging wall jet pressure, it was assumed that the jet issuing from an air-knife is similar to the Hiemenz plane stagnation flow, and the wall shear stress could be predicted by an equation using the assumption of a non-negative Gaussian profile in impinging wall jet pressure in general, so that it cannot be reliable for some impinging wall jet regions and nozzle systems intrinsically. Nevertheless, one cannot find a suitable method to cope with the difficulties in measuring/calculating of the shear stress and the impinging wall jet pressure. Such a difficulty which will cause an inaccuracy in the coating thickness prediction. With these connections, in the present study, we suggest a new method named as a two-step calculation method to calculate the final coating thickness, which consists of the air jet analysis and coating thickness calculation. And, from the comparison of the results one may confirm the validation of the new suggested method.     

钻杆外壁清洗射流流场的数值分析

在采用高压水射流清洗钻杆外壁过程中,为了得到最佳的清洗位置和清洗角度,必须提高钻杆的清洗效率和质量,文章建立了外部射流流场控制方程组,结合标准的k-ε湍流模型进行化简求解,采用ICEM CFD建立网格模型,通过Fluent软件采用VOF气液两相流模型和SIMPLE算法对喷嘴外部流场进行数值模拟分析。在一定的喷射范围内,改变喷射角度模拟对钻杆外壁的理论清洗情况,在最佳的清洗情况下确定喷头在整个清洗装置中的安装位置和喷射角度。分析结果表明:在600mm的安装距离中,随着喷射角度的减小,射流束的分流情况越来越明显,当减小到15°时,流束基本朝向一边;该喷射范围内,随着轴线位置的增大,速度和压力都呈现衰减状态,当距离超过500mm,速度衰减较明显,所以适宜的喷射距离为500mm;当喷射角度除15°和90°时衰减较大外,其余角度下衰减情况基本相同。再通过对壁面打击力的分析得出最佳的喷射角度为60°。     

喷嘴宽度对偏转板射流阀射流效率影响的仿真分析

利用Pro/E和Fluent软件对不同λ₁(喷嘴宽度D₁与导流窗口最小宽度H₁的比值)的偏转板射流阀进行几何建模与流场仿真,得到不同λ₁ 下偏转板射流阀内部射流速度、压力云图和射流流场的速度、压力分布特征;通过分析仿真数据得到λ₁对供油流量Q_S、射流流量Q_J、射流流量效率η_J的影响规律。研究发现,喷嘴喷射出的部分油液由于受到V形导流斜面的作用沿着V形导流斜面反向运动,从而使喷向接收口的有效射流流量减小,同时在偏转板入口两侧出现漩涡和能量损失;随着λ₁增大,供油流量Q_S近似线性增大,而射流流量Q_J先增大后又减小;当λ₁=1时射流流量Q_J取得最大值12.5 kg/s,对应的射流流量效率η_J最大为77.6%。研究结果为偏转板射流伺服阀的效率提高及结构优化设计提供理论依据与参考。     

Measurement of turbulent supersonic steam jet flow characteristics using TDLAS

Ejectors have no moving parts and are preferable to mechanical compressors in many applications, but ejectors typically have a relatively low efficiency. To aid in the ejector design process, thorough understanding of the turbulent mixing of multi-phase compressible jets is beneficial.This paper reports experimental results for Tunable Diode Laser Absorption Spectroscopy (TDLAS) measurements derived from an axisymmetric supersonic steam jet apparatus.In this experimental work, a supersonic steam jet nozzle exit of a diameter 13.6 mm was surrounded by a low-speed flow of dry nitrogen. The TDLAS system was traversed through the flow at three different planes downstream from the ejector nozzle exit: 15, 20, and 30 mm distance. At each of the three planes, line-of-sight measurements were made with the laser passing through locations between 0 and 15 mm from the jet centreline.Through the analysis of the TDLAS data and application of the Abel inversion method, the radial distribution of the pressure, temperature, and the concentration of the water-vapour were obtained. The key findings are that it is possible to determine key physical parameters using experimental TDLAS measurements when combined with a suitable numerical optimization approach.     

柴油机燃烧室匹配参数对撞壁喷雾特性的影响

利用高速纹影摄像技术,研究了喷油器喷孔角度、喷孔与活塞顶面间的撞壁距离、燃烧室缩口半径和凸台夹角对柴油撞击燃烧室壁面后喷雾特性的影响。研究结果表明,试验条件下适宜的喷孔角度为75°,增大喷孔角度可以促进喷雾撞壁后的油气混合,但是喷孔角度过大会增加油束撞击气缸盖和气缸套的风险;适宜的撞壁距离为4.2mm,即压缩上止点前15°CA（CA指曲轴转角）,较小的撞壁距离会促进喷雾液滴在凹坑区域的碰撞与黏结,而较大的撞壁距离不利于燃烧室中心区域的空气利用;此外,适当增大缩口半径可以促进燃油与空气的混合,减小燃烧室壁面的燃油湿壁面积;改变凸台夹角可以控制撞壁后喷雾在燃烧室中心区域的扩散速度。     

双腔室自振脉冲喷嘴空化射流数值模拟

以风琴管喷嘴为基础,串联一个谐振腔形成双腔室自激振荡脉冲喷嘴,利用Fluent对其流场进行数值模拟,分析射流靶距、二级谐振腔腔长比、腔径比的变化对空化射流流场的影响。结果表明：谐振腔尺寸过大或过小均会影响涡环结构的形成,进而影响空化效果。当谐振腔腔长比为0.77、腔径比为2.6时,谐振腔内涡环结构对称性好,轴向含气率高,射流速度较高,该结构利于清洗效率的提高。靶面滞止压力可对空化效果产生影响。当射流靶距较小时,在滞止压力的作用下二级谐振腔无涡环结构产生,轴向含气率较低。当靶距增加到18 mm时滞止压力产生的影响减小,轴向含气率明显提高,因此清洗靶距应至少为18 mm。但靶距的增加会降低射流到达靶面的动能,因此最佳靶距应取18 mm。     

新型钢板桩液力自旋式喷嘴设计及流场分析

针对钢板桩遇密实土层难以沉桩的问题,设计了一种新型液力自旋式喷嘴结构。基于流体力学理论,利用Fluent软件,通过改变斜射流口的偏心距、斜射流口与水平面的夹角等结构参数,得到了该喷嘴内腔的压力、流速及旋转体转矩的变化规律。结果表明:随着偏心距的增大,旋转体转矩增大;斜射流口的出口平均流速在小偏心距变化微小,在大偏心距逐渐减小;随着水平夹角的增大,旋转体转矩减小;斜射流口的出口平均流速随着水平夹角的增大先增大后减小,且随着偏心距的增大其峰值点逐渐后移。     

Feedback mechanism of low-speed edgetones

A feedback mechanism of low-speed edgetones is analyzed by using the jet edge interaction model in which reaction of the edge is regarded as an array of dipoles. From the jet-edge interation model the surface pressure of the edge and the upstream wave are estimated by assuming the downstream disturbance as a sinuously oscillating flow with a constant convection speed. The surface pressure distribution on the edge is found to increase from zero at the tip to a peak value around a quarter wavelength downstream, which may be regarded as an effective source point of the upstream-propagating sound wave. From the condition that the two wave trains should be phase-locked at the nozzle lip, the phase factorp is found to be in the range, −1/2<p<0, in the phase criterion of the form,h/A+h/λ=n+p, where h is the stand-off distance.A and λ the wavelengths of downstream and upstream respectively, andn the stage number. From the existing experimental data the phase factor is estimated on the basis that the convection wavelength is dependent only upon the mean jet velocity and the frequency, but not upon the stage number. The experimental values are in the same range of the theoretical estimation indicating that the phase factor is not a universal constant but varies in the range, −1/2<p<0, depending on the nozzle-edge configuration and the flow condition.     

An experimental study of the nozzle lip thickness effect on supersonic jet screech tones

It is well known that screech tones of supersonic jet are generated by a feedback loop driven by the instability waves. Near the nozzle lip where the supersonic jet mixing layer is receptive to external excitation, acoustic disturbances impinging on this area excite the instability waves. This fact implies that the nozzle lip thickness can influence the screech tones of supersonic jet. The objective of the present study is to experimentally investigate the effect of nozzle-lip thickness on screech tones of supersonic jets issuing from a convergent-divergent nozzle. A baffle plate was installed at the nozzle exit to change the nozzle-lip thickness. Detailed acoustic measurement and flow visualization were made to specify the screech tones. The results obtained obviously show that nozzle-lip thickness significantly affects the screech tones of supersonic jet, strongly depending on whether the jet at the nozzle exit is over-expanded or under-expanded.     

Method of setting Nozzle intervals at the finishing scale breaker

The scale is removed from the strip by high pressure hydraulic descaling at the FSB(Finishing Scale Breaker). Recently, the spray height of nozzle has a trend to be shorter for the purpose of increasing the impact pressure by the high pressure water jet. Here, the nozzle intervals should be decided after considering the impact pressure and the temperature distribution on the strip. In other words, the minimum of impact pressure at the overlap of spray influences the surface grade of the strip due to scale and the overlap distance of the spray affects the temperature variation in the direction of the width of strip. In the present study, the impact pressure of the high pressure water jet is measured by the hydraulic descaling system and calculated with regard to the lead angle of 15° and the offset angle of 15°, and then the temperature distribution and the temperature variation are calculated at the overlap distances of 0 mm, 10 mm, 20 mm, and 30 mm, respectively. The method of setting nozzle intervals is shown by utilizing these results.     

Numerical analysis for the coating thickness prediction in continuous hot-dip galvanizing

Gas wiping is a decisive operation in the hot-dip galvanizing process. Especially, it has a crucial influence on the thickness and uniformity of coating film, but may be subsequently responsible for splashing. To date, the number of fundamental studies on the jet structure impinging on a vertical moving strip for various nozzle systems has not been sufficient to draw any meaningful conclusion. In this connection, at first, to confirm the validation of numerical analysis, the impinging jet pressure on the surface of a vertical strip by experiment is compared with the results by numerical analysis. Next, after confirming for the superiority of a constant expansion rate nozzle in splashing, the relationship between the stagnation pressure and the impinging jet pressure distribution issuing from the nozzle system of constant expansion rate is investigated. Finally, by using the calculated wall shear stress, the relationships among the coating thickness, strip speed and nozzle stagnation pressures are clarified. It is found that the impinging wall pressure for the case of constant expansion rate nozzle is more favorable for the problem of splashing to the case of the conventional one. Furthermore, from the point of view of energy conservation, it is advisable to use a constant expansion rate nozzle as a gas-wiping nozzle.     

Turbulent mixing flow characteristics of solid-cone type diesel spray

The intermittent spray characteristics of the single-hole diesel nozzle (d_n=0.32 mm) used in the fuel injection system of heavy-duty diesel engines were experimentally investigated. The mean velocity and turbulent characteristics of the diesel spray injected intermittently into the still ambient were measured by using a 2-D PDPA (phase Doppler particle analyzer). The gradient of spray half-width linearly increased with time from the start of injection, and it approximated to 0.04 at the end of the injection. The axial mean velocity of the fuel spray measured along the radial direction was similar to that of the free air jet within R/b=1.0-1.5 regardless of elapsing time, and its non-dimensional distribution corresponds to the theoretical velocity distributions suggested by Hinze in the downstream of the spray flow fields. The turbulent intensity of the axial velocity components measured along the radial direction represented the 20-30% of the Ū_cl and tended to decrease in the outer region. The turbulent intensity in the trailing edge was higher than that in the leading edge.     

负压排屑装置楔形结构优化设计与仿真

为解决超大长径比深孔加工排屑困难问题,在分析DF系统负压排屑作用机理的基础上,建立负压射流模型,通过采用填充部分前/后分离区所占区域的方法,设计了一种位于射流喷嘴处的楔形结构,以减少前/后分离区的能量损耗。理论计算及Fluent仿真优化实验结果表明,该楔形尺寸在长度L1=75 mm、宽度L2=1 mm时效果最好,切削液流速增大约10.07%,湍流动能增大约11.39%,负压区压力值减小约79.26%,该楔形结构提高了负压排屑能力,最大程度地减少了前/后分离区的能量损耗。     

径向水平井自进式旋转射流钻头流场特性分析

为解决径向水平井钻进过程中破岩效率和自进能力的问题,设计了一种自进式旋转射流钻头。运用数值模拟方法,采用RNG k-ε湍流模型对所设计射流钻头的内外流场进行了三维流动特性分析,并分析了射流钻头结构参数对喷嘴流场特性的影响规律,进一步优化了自进式旋转射流钻头。结果表明,自进式旋转射流喷嘴外流场的轴心速度在喷嘴中心线上的速度最大,随着径向半径的增大,轴向速度迅速减小;切向速度沿喷嘴径向呈现出经典的"N"形分布,有利于增大射流破碎岩石的深度和破碎面积;径向速度呈轴对称分布,存在明显的漫流层,有助于岩屑的脱离;自进式旋转射流钻头导向叶轮的螺距和导叶数量,对射流速度有着重要的影响;喷嘴直径对射流流场特性的影响较大。经过优化,得到射流钻头的叶轮螺距16mm,导叶数为2,喷嘴直径为1mm。     

Effect of boundary layer swirl on supersonic jet instabilities and thrust

This paper reports the effects of nozzle exit boundary layer swirl on the instability modes of underexpanded supersonic jets emerging from plane rectangular nozzles. The effects of boundary layer swirl at the nozzle exit on thrust and mixing of supersonic rectangular jets are also considered. The previous study was performed with a 30° boundary layer swirl (S=0.41) in a plane rectangular nozzle exit. At this study, a 45° boundary layer swirl (S=1.0) is applied in a plane rectangular nozzle exit. A three-dimensional unsteady compressible Reynolds-Averaged Navier-Stokes code with Baldwin-Lomax and Chien’sk-ε two-equation turbulence models was used for numerical simulation. A shock adaptive grid system was applied to enhance shock resolution. The nozzle aspect ratio used in this study was 5.0, and the fully-expanded jet Mach number was 1.526. The “flapping” and “pumping” oscillations were observed in the jet’s small dimension at frequencies of about 3,900Hz and 7,800Hz, respectively. In the jefs large dimension, “spanwise” oscillations at the same frequency as the small dimension’s “flapping“ oscillations were captured. As reported before with a 30° nozzle exit boundary layer swirl, the induction of 45° swirl to the nozzle exit boundary layer also strongly enhances jet mixing with the reduction of thrust by 10%.     

近距离淹没冲击射流动态流场特性

近距离下淹没冲击射流具有重要的应用前景,但有关其动态流场特性的研究尚不充分。利用粒子图像测速技术(Particle image velocimetry,PIV)对冲击距离为H/D=1时的动态流场特性进行测量,研究雷诺数Re和喷嘴端面轮廓(壁面约束)对间隙内旋涡生成的影响,并对试验数据进行涡量分析与本征正交分解方法(Proper orthogonal decomposition,POD)分析。结果表明,雷诺数Re对不同喷嘴端面轮廓(壁面约束)的旋涡生成和迁移影响规律不同。雷诺数对直角型喷嘴的双涡环模式流态影响较小,但对圆角型喷嘴卷吸流态影响较大,且随雷诺数的增大流场出现动态对称涡旋,该对称涡旋逐渐向间隙外迁移且呈现出明显的周期性变化特征。涡量分析得到时均场的涡量大小与分布情况,通过与POD分析中瞬态场的含能大尺度结构分布相结合,揭示间隙外涡旋能量的来源与变化规律。通过前4阶瞬态脉动速度场重构,可以从微观时间尺度进一步说明瞬态速度场的突变性与周期性。研究成果将有助于加深对冲击射流本质的理解。     

The self-induced oscillations of the under expanded jets impinging upon a cylindrical body

The present study addresses the flow characteristics involved in the self-induced oscillations of the underexpanded jet impinging upon a cylindrical body. Both experiment and computational analysis are carried out to elucidate the shock motions of the self-induced oscillations and to find the associated major flow factors. The underexpanded sonic jet is made from a nozzle and a cylindrical body is placed downstream to simulate the impinging jet upon an obstacle. The computational analysis using TVD scheme is applied to solve the axisymmetric, unsteady, inviscid governing equations. A Schlieren system is employed to visualize the self-induced oscillations generated in flow field. The data of the shock motions are obtained from a high-speed video system. The detailed characteristics of the Mach disk oscillations and the resulting pressure variations are expatiated using the time dependent data of the Mach disk positions. The mechanisms of the self-induced oscillations are discussed in details based upon the experimental and computational results.