Corner Flow Control in High Through-Flow Axial Commercial Fan/Booster Using Blade 3-D Optimization

This study is aimed at using blade 3-D optimization to control corner flows in the high through-flow fan/booster of a high bypass ratio commercial turbofan engine. Two kinds of blade 3-D optimization, end-bending and bow, are focused on. On account of the respective operation mode and environment, the approach to 3-D aerodynamic modeling of rotor blades is different from stator vanes. Based on the understanding of the mechanism of the corner flow and the consideration of intensity problem for rotors, this paper uses a variety of blade 3-D optimization approaches, such as loading distribution optimization, perturbation of departure angles and stacking-axis manipulation, which are suitable for rotors and stators respectively. The obtained 3-D blades and vanes can improve the corner flow features by end-bending and bow effects. The results of this study show that flows in corners of the fan/booster, such as the fan hub region, the tip and hub of the vanes of the booster, are very complex and dominated by 3-D effects. The secondary flows there are found to have a strong detrimental effect on the compressor performance. The effects of both end-bending and bow can improve the flow separation in corners, but the specific ways they work and application scope are somewhat different. Redesigning the blades via blade 3-D optimization to control the corner flow has effectively reduced the loss generation and improved the stall margin by a large amount.

Interior corner flow theory and its application to the satellite propellant management device design

The interior comer flow theory is fundamental for liquid management in space. In this paper, the interior comer flow theory is modified by correction of the curvature and shape parameters based on geometry relationship, so that it can be extended to a wide range of applications including different dihedral angles and contact angles. This modification is validated with the data provided by the references using capillary tube and drop tower. Besides, the errors between the theory and experiment value are analyzed for the case of small viscosity and the long-time flow, finding that the main reason causing the error is the transformation of the flow resistance along the flow path. At last, the theory of interior comer flow is applied to the primary design of the Propellant Management Device in satellite tank, and optimum design of the vanes is given in terms of maximum flow rate.

Numerical study of compression corner flowfield using Gao-Yong turbulence model

A numerical simulation of shock wave turbulent boundary layer interaction induced by a 24° compression corner based on Gao-Yong compressible turbulence model was presented.The convection terms and the diffusion terms were calculated using the second-order AUSM(advection upstream splitting method) scheme and the second-order central difference scheme,respectively.The Runge-Kutta time marching method was employed to solve the governing equations for steady state solutions.Significant flow separation-region which indicates highly non-isotropic turbulence structure has been found in the present work due to intensity interaction under the 24° compression corner.Comparisons between the calculated results and experimental data have been carried out,including surface pressure distribution,boundary-layer static pressure profiles and mean velocity profiles.The numerical results agree well with the experimental values,which indicate Gao-Yong compressible turbulence model is suitable for the prediction of shock wave turbulent boundary layer interaction in two-dimensional compression corner flows.

Study on asymmetric interior corner flow in microgravity condition

The capillary flow in asymmetric interior corner consisting of straight vane and curved wall is studied with analytical solution.The concept of equivalent interior corner angle is proposed to convert the asymmetric interior corner model into symmetric interior corner model.Then the governing equations of interior corner flow are established,and based on which the interior corner flow is calculated.This method is used to analyze the capillary flow in cylindrical vane-type surface tension tank with outer vanes.The research can provide beneficial reference to the design of vane-type surface tension tank.

Calibration of Modified Spalart-Ailmaras Model Parameters for Linear Compressor Cascade Corner Flow

In this study,Bayesian parameter calibration is applied to Saplart-Allmaras(SA)turbulence model,and the prediction improvement by the calibrated model is demonstrated.The quantity of interest(QOI)is the pitch-wise distribution of Mach number in the comer separation flow region.The 10 model parameters included in the SA model with Rotation-Curvature correction are considered as random variables obeying uniform prior probability distributions.The order of generalized Polynomial Chaos(gPC)used for sensitivity analysis and surrogate model in calibration is incrementally increased during the calibration process.Posterior convergence is obtained at the 3rd order expansion level in this study.At this final level,sensitivity analysis indicates 3 model parameters,cbl,k and cr3 are the most influential random variables,and 3-parameter Bayesian calibration is conducted.The likelihood function in the Bayesian theorem is specified in the form of Gaussian distribution,including experimental uncertainty.The combination of prior and likelihood brings the posterior distribution of model parameters,and Maximum A Posterior(MAP)value is selected as a calibrated parameter set.The flow simulation with calibrated parameters shows a significant increase in the accuracy of the Mach number profile in the comer separation region.The increase in accuracy is attributed to enlarged turbulent viscosity due to the parameter modification of the turbulent viscosity source term.The calibrated parameter is also tested in the off-design flow field,not included in the calibration process.The calibrated CFD again shows improved accuracy for comer separation prediction,and the effectiveness of the parameter set outside of the calibration field is demonstrated.

QUASI－FLOW CORNER THEORY ON LARGE PLASTIC DEFORMATION OF DUCTILE METALS AND ITS APPLICATIONS

A quasi -flow corner theory on lalge plastic deformation if ductile metals is proposed in this paper. From orthogonal rule of plastic flow, the theory introduces a 'modulus rethtced function' and a corner effect of yield surface into the constilulive model of elastic-plastic large deformation . Thereby, the smooth and continuous transitions from orthogonal constitutive model to non-orthogonal one, and from plastic loading to elastic unloading are realized. In addition, the theory makes it possible to connect general anisotropic yield functions with corner hardening effect. The comparison between numerical simulation and experimental observation for the uniaxial tensile instability and shear band deformation of anisotropic sheet metals shows the validity of the present quasi-flow corner theory.

光流结合特征提取的室内机器人避障技术研究

为解决室内机器人正向准确避障问题,提出一种光流结合特征提取的视觉避障方法。将LK光流与多尺度思想结合,加入仿射变换,提高算法追踪角点的噪声鲁棒性,进而准确检测视场中的障碍物;通过评估障碍物风险程度,制定出碰撞时间(TTC)结合光流平衡策略的碰撞机制,引导机器人在无碰路径上移动。改进光流与特征提取结合能提高相机快速运动下的追踪成功率,制定的碰撞策略能够有效规避机器人前方的障碍物。实验表明,相机快速运动时,算法能提高追踪的准确性,有效检测出视场中的障碍物,引导机器人无碰撞行驶,具备较强的独立性和实时性。

90°转角微流道内导流板应用特性数值研究

改善转角微流道内流体的二次流特性对提高微流体传输的可靠性具有重要意义。针对90°转角矩形截面微流道,本文提出在微流道转角处增加导流板来实现该区域二次流的主动调节和控制。本文设计了圆弧型和弧—直组合型两种导流板结构,建立了五种不同结构微流道模型,开展了流场对称性和Dean涡分析,流体相对横向动能ksec和流道局部阻力系数ζ90°计算。结果表明,导流板结构能有效改善微流道转角区的流场对称性,加速Dean涡的消失,降低二次流强度,同时也会引起流体流动局部阻力系数有所增加。

神东矿区新型无机膏体防灭火充填材料制备及性能研究

为解决神东矿区回采工作面两端巷道附近采空区遗煤多、易自燃、难封堵的难题,提出一种新型无机膏体防灭火充填材料,高效快速充填回采工作面上下隅角。采用神东矿区附近易获取的粉煤灰、炉渣和P·O·42.5硅酸盐水泥作为膏体主要原料,通过室内实验对材料的物理性质和化学成分进行研究,并通过膏体流动性、凝固特性、膨胀特性、充填体强度测试实验,确定出膏体最佳材料配比及外加剂参量。实验结果表明:炉渣基膏体具有良好自膨胀性,7 d自膨胀率可达5.6%,且初凝时间短,满足工程所需强度要求;膏体防灭火材料的最佳配比方案为水泥∶粉煤灰∶炉渣=1∶4∶20,质量分数为78%,J85型速凝剂的添加量为6%。工程应用表明:采用优选的膏体充填材料进行隅角充填封堵后,采空区漏风量整体下降至充填前的30%,CO体积分数从120×10^(-6)降至46.5×10^(-6),O2体积分数在深入采空区走向长度约80 m处降至10%以下,采空区内“散热带+氧化带”的走向长度由未充填前的160 m缩短为80 m。

NUMERICAL SIMULATION OF WING-BODY JUNCTION TURBULENCE FLOW

Wing-body junction turbulence flow is simulated by using RANS equation and boundary fitted coordinate technique. Three order differential scheme is used in the computation of convection term and two layers turbulence model are employed in the calculation.

基于拟流动角点理论的铝合金板成形仿真方法

金属板材冲压技术已经广泛用于运载工具薄壁结构的成形制造,而有限元仿真方法能够有效缩短新成形工艺的研发周期。为保证金属板材成形预测的有效性,基于拟流动角点本构理论建立了适用于数值仿真的应力更新方法。采用半隐式返回映射算法将拟流动角点本构理论与考虑材料轧制各向异性的Barlat'89屈服准则相结合(QF-Barlat'89),通过编写材料子程序VUMAT,实现了本构模型在有限元分析软件Abaqus中的应用。通过对单个单元的受力特征进行对比,验证了算法的准确性。进一步对AA5052-O铝合金试样的单向拉伸及圆筒拉深成形工艺进行了仿真预测,并分析了板材尺寸对成形质量的影响。结果表明,QF-Barlat'89本构模型可以对板材的失效位移、减薄量和应变分布等成形特征进行有效预测,适用于金属板材冲压成形工艺的仿真研究。

端壁自适应射流对跨声速压气机近失速工况性能影响的数值研究

为了提升压气机的稳定工作裕度和近失速工况性能,提出了一种在压气机静叶端壁施加端壁自适应射流的被动控制方法。利用数值模拟方法开展了不同出口轴向位置和出口偏航角的端壁自适应射流结构对跨声速压气机级性能影响的研究。研究结果表明:端壁自适应射流结构能够有效提升压气机的稳定工作裕度,并能提高近失速工况的总压比和等熵效率,在目前综合表现最佳的端壁自适应射流方案中,稳定工作裕度改进量为27.99%,近失速工况的总压比和等熵效率分别提升了0.61%和1.07%,峰值点效率略微下降0.55%。端壁自适应射流结构能够在一定程度上抑制低能流体回流,缓解流道堵塞,降低总压损失,提升叶片负荷,射流出口位于角区分离起始位置附近的作用效果较好。

不同雷诺数下4∶1圆角矩形柱气动力特性及流场数值模拟研究

圆角化处理的矩形柱绕流具有复杂的气动力和流场特性。为深入了解圆角矩形柱的雷诺数(Reynolds number, Re)效应,采用基于计算流体力学(Computational fluid dynamics, CFD)的大涡模拟(Large eddy simulation,LES)方法,开展了不同Re下宽高比4∶1圆角矩形柱绕流数值模拟,研究了不同Re下圆角矩形柱的气动力系数、斯特劳哈尔数(Strouhal number, St)、风压系数和流场等变化规律。结果表明:表面风压和时均流场在Re≤4×10^(3)时,Re效应显著,但当Re>4×10^(3)时,Re效应较弱。当Re≤4×10^(3)时,升力系数均方根和平均阻力系数随着Re先增大后减小,在Re=1×10^(3)时达到最大;而St先增大后减小再增大,分别在Re=2×10^(3)时达到最大,在Re=4×10^(3)时达到最小。回流长度随着Re先减小后增大,尾流旋涡中心逐渐后移。

基于改进ORB算法的油水两相流油泡匹配方法

ORB算法能够快速匹配油水两相流中的油泡。相比SIFT算法和SURF算法,ORB算法拥有无可比拟的速度优势。然而,ORB算法匹配油泡的过程中,存在油泡匹配准确率低、角点提取速度慢、角点数量少等缺陷,降低了油速测量的准确度。为提升油泡匹配准确率和油速测量准确度,对ORB算法进行如下改进:角点提取方面,通过Shi-tomasi角点响应算法替代Harris角点响应算法,加快角点提取速度;通过对角点之间最小距离d值的探索优化,确定最佳d值,使Os区域,即油水两相流图像中不明显油泡所在的区域,能有效提取到角点,增加角点数量,同时优化角点分布。油泡匹配方面,在RANSAC算法基础上,融入GMS算法,进行RANSAC-GMS双重去除误匹配对,提高油泡匹配准确率,最大限度保留正确匹配对,提升正确匹配对数量。实验结果表明:改进的ORB算法在提取角点耗时上缩短至原始ORB算法的37%;角点数量是原始ORB算法的1.9倍;正确匹配对数量是原始ORB算法的2.3倍。改进的ORB算法提高了油泡匹配准确率。最后,基于改进的ORB特征点匹配的PTV算法对油速进行测量,实验结果表明油速测量准确度达94.0%,提升26.5%,能够用于实际油速测量。

某内河航道整治工程凸角裁弯方案研究

结合实际工程案例,为确定转向角度大的两条航道交汇处的碍航凸角裁弯方案,在根据规范进行尺度论证的基础上,结合数学模型,对各方案的水沙条件变化情况进行预测分析。裁弯后,河段整体冲淤趋势未发生明显改变,裁弯附近河段随着挖深及疏浚面积的增大,回淤量随之增加,但总体回淤强度不大;横流明显减小,弯曲航道航行条件得到改善,船舶转弯半径更大,航行视路更开阔,有利于船舶操纵与航行安全。裁弯工程已按本文所荐及优化方案实施完成,可供类似工程借鉴和参考。

切圆燃烧锅炉深度调峰工况下燃烧器出口风速变化特性分析

为有效改善炉膛内的空气动力场特性,对某300 MW锅炉设备及运行参数进行理论计算分析,研究了四角切圆燃烧锅炉在设计工况与深度调峰工况下燃烧器出口一次风速、二次风速、二次风与一次风动量比的变化特性。结果表明深度调峰工况下的燃烧器出口一次风速与热耗率验收(turbine heat acceptance,THA)工况设计值相比仅小幅下降,而燃烧器出口二次风速却出现了大幅下降,从而使得二次风与一次风的动量比显著降低,二次风对炉膛空气动力场的组织能力显著下降。根据计算结果可知,随着锅炉负荷的下降,未投运燃烧器层数越多,对炉膛空气动力场的影响越小;未投运燃烧器层冷却风量越大,对炉膛空气动力场的影响越大。

Linear Plus Linear Fractional Capacitated Transportation Problem with Restricted Flow

In this paper, a transportation problem with an objective function as the sum of a linear and fractional function is considered. The linear function represents the total transportation cost incurred when the goods are shipped from various sources to the destinations and the fractional function gives the ratio of sales tax to the total public expenditure. Our objective is to determine the transportation schedule which minimizes the sum of total transportation cost and ratio of total sales tax paid to the total public expenditure. Sometimes, situations arise where either reserve stocks have to be kept at the supply points, for emergencies or there may be extra demand in the markets. In such situations, the total flow needs to be controlled or enhanced. In this paper, a special class of transportation problems is studied where in the total transportation flow is restricted to a known specified level. A related transportation problem is formulated and it is shown that to each basic feasible solution which is called corner feasible solution to related transportation problem, there is a corresponding feasible solution to this restricted flow problem. The optimal solution to restricted flow problem may be obtained from the optimal solution to related transportation problem. An algorithm is presented to solve a capacitated linear plus linear fractional transportation problem with restricted flow. The algorithm is supported by a real life example of a manufacturing company.

Mode transition and oscillation suppression in supersonic cavity flow

Supersonic flows past two-dimensional cavities with/without control are investigated by the direct numerical simulation （DNS）. For an uncontrolled cavity, as the thickness of the boundary layer declines, transition of the dominant mode from the steady mode to the Rossiter Ⅱ mode and then to the Rossiter III mode is observed due to the change of vortex-corner interactions. Meanwhile, a low frequency mode appears. However, the wake mode observed in a subsonic cavity flow is absent in the current simulation. The oscillation frequencies obtained from a global dynamic mode decomposition （DMD） approach are consistent with the local power spectral density （PSD） analysis. The dominant mode transition is clearly shown by the dynamic modes obtained from the DMD. A passive control technique of substituting the cavity trailing edge with a quarter-circle is studied. As the effective cavity length increases, the dominant mode transition from the Rossiter Ⅱ mode to the Rossiter Ⅲ mode occurs. With the control, the pressure oscillations are reduced significantly. The interaction of the shear layer and the recirculation zone is greatly weakened, combined with weaker shear layer instability, responsible for the suppression of pressure oscillations. Moreover, active control using steady subsonic mass injection upstream of a cavity leading edge can stabilize the flow.

大学生方程式赛车过弯非稳态气动问题的数值与试验研究

以大学生方程式赛车为研究对象,采用非稳态来流仿真方法对其过弯时的气动性能展开了研究。采用非稳态来流方法,将仿真来流速度设置为随时间变化的场函数以精准模拟入弯情形,并与稳态来流的弯道仿真结果进行了对比;配合仿真结果,在道路试验中使用表面压力测量对扩散器和尾翼的局部流场进行了量化。结果表明:赛车前轮以及前翼在非稳态过弯时会对下游底部流场产生较大影响,底部扩散器的非稳态气动鲁棒性将是整车气动设计的重点。

轴向间距对矿用旋风机旋转失速性能的影响

矿用对旋风机在小流量工况运行时极易出现旋转失速现象,严重影响其运行稳定性。采用SST k-ω湍流模型,对FBCDZ-10-No20型对旋风机在5种轴向间距下全流道内的非定常流动进行数值模拟,研究了轴向间距对矿用对旋风机失速过程的影响,揭示了不同轴向间距时的失速起始与发展机理。结果表明:轴向间距对失速起始扰动的首发位置、表现形式和发展过程都具有显著影响。对于70、100 mm两种轴向间距,失速起始扰动均首发于前级叶顶,随后在两级叶轮之间的动−动干涉作用下,后级叶顶也出现失速起始扰动,但与70 mm的轴向间距相比,当轴向间距为100 mm时,动−动干涉效应相对较弱,使得后级出现失速起始扰动需要更长的时间。对于140、170、225 mm三种轴向间距,失速起始扰动均是首先发生在后级叶根区域,不同的是140 mm间距时,前级叶顶泄漏流不能完全随主流流出通道,而是形成了局部叶顶堵塞区;而对于170、225 mm两种间距,前级叶顶则几乎没有堵塞区,最终仅在后级形成了成熟的失速涡团。随着轴向间距的增大,由前级叶顶泄漏流发生前缘溢流及尾缘反流形成的堵塞区逐渐缩小,而由后级叶根吸力面径向涡流形成的堵塞区则逐渐增大,当前级叶顶泄漏流无法形成堵塞区时,失速类型就由前级叶顶泄漏流诱发的“突尖型”转变为由后级叶根径向涡流诱发的“局部喘振型”。