合成射流与主流相互作用的数值研究

本文采用动网格技术,利用大涡模拟求解三维N-S方程,对直射流以及倾斜角为30°的斜射流进行了三维数值模拟。数值模拟结果表明:数值模拟的直射流出口速度曲线与理论速度曲线吻合较好,通过直射流与斜射流对比发现,直射流产生的涡环为对称涡环,而斜射流的为不对称涡环;直射流射流出口时均速度影响范围大于斜射流,但是其射流宽度小于斜射流射流宽度。本文还分析了射流与主流的相互作用,数值模拟了不同主流速度下射流的运动状态,结果表明:主流速度为2.0 m/s时,直射流产生的涡环受到主流的作用发生倾斜,斜射流产生的涡环由于主流的作用,变成典型的马蹄涡形式;由于射流对主流的影响,直射流对主流速度起阻碍作用,减缓了边界层及附近主流的速度,斜射流加速了主流边界层内的流体速度,使边界层速度更加饱满;随着主流速度的提高,射流产生的涡环被主流吹扫进入边界层,在壁面上发生破裂,与边界层内流体混合,射流对主流的的影响减弱。     

带冷气喷射叶栅内三维流场控制方程的研究

推导出适用于带冷气喷射的涡轮叶栅内三维流动的控制方程，得出任意曲线坐标系下守恒型Ｎ－Ｓ方程和Ｅｕｌｅｒ方程的表达式，对熵的分析表明冷气与主流气体之间的焓差和速度差是冷气喷射引起熵变化的主要因素。     

绕水翼间隙涡结构形成机理与间隙几何影响

为了分析绕水翼间隙涡结构形成机理和探究压力边圆角几何的影响,对绕NACA0009水翼间隙流动进行数值计算. 通过流线涡量云图三维可视化分析,得到间隙流动特征及涡结构,对涡强度进行对比. 对翼形中截面间隙进出口边速度和间隙区平面流线、压力、湍动能进行比较分析. 研究发现：直角叶顶水翼泄漏流在间隙进口边有较大的展向速度,在间隙内形成新月形分离区,在逆压梯度作用下形成叶顶分离涡（TSV）,涡尺度与展向速度成正相关;叶顶泄漏涡（TLV）形成源于间隙出口边射流与吸力边侧低速流体之间的持续剪切作用,低速流体从剪切层获得持续的能量输运形成稳定的泄漏涡结构;间隙压力边圆角对TSV起抑制作用,降低了间隙区整体涡强度.     

横向椭圆射流的大涡模拟

为探索大型电站锅炉横向再燃射流的穿透性，采用大涡模拟方法分别计算了射流速度比率为10的横向圆管湍流射流和椭圆湍流射流，基于射流速度50 m/s的雷诺数为16 600.模拟结果表明，圆管射流中心轨迹与试验数据基本一致，方向因子为0.3的椭圆射流的穿透能力远大于圆管射流穿透力.计算捕捉到了射流上游由开尔芬 亥姆霍兹不稳定性引起的剪切层涡卷、始于近场并主宰远场的逆向旋转涡对和圆管射流尾涡区的垂直上升尾涡.与圆管射流相比，椭圆射流的剪切层涡卷的强度大大减弱，逆向旋转涡对狭长对称，尾涡区的垂直上升尾涡并不明显，这是椭圆射流穿透力提高的主要原因.     

气雾射流动态传热实验研究

设计搭建了气雾射流动态传热实验装置,建立了二维非稳态导热反问题模型,研究了表面温度和表面热流密度的时间分布.结果表明在冷却过程中缸体穿越喷射区与淌水区历经了几个不同的换热阶段,温度曲线出现了明显的周期性的特点,成功的模拟了连铸二冷气雾冷却周期性换热的特征.     

不同孔型气膜冷却流场的大涡模拟

采用大涡模型(LES)模拟了圆形气膜孔和锥形角γ=30°扇形孔在吹风比M=1.0时不同截面上的涡量等值线以及分布特征随时间的变化过程。结果表明:对称面的正反旋涡和垂直截面的马蹄形涡的两翼交替周期性地脱落成新的涡,同一截面扇形气膜孔旋涡生成和脱落的时间比圆形气膜孔的短,冷气射流与主气流掺混剧烈,带走的能量较多,所以壁面的冷却效率高;反向旋涡对气膜冷却流场有重要影响,在同一截面圆形孔的反向涡旋对(CVP)要比扇形孔的大,且涡心位置要比扇形孔的高,因此圆孔对壁面的冷却效果要比扇形孔的差。     

微磨料气射流加工机理实验研究

微磨料气射流加工技术是对硬脆材料进行微细加工的一种非常有潜力的技术.对脆性材料微磨料气射流加工机理的实验研究是精细精密加工领域一个重要研究方向.为研究微磨料气射流加工的一般机理,在一套自制微磨料气射流装置上实验并分析了喷射参数及磨料参数对微磨料气射流加工影响的数据,得到了微磨料气射流加工中喷射距离、喷射时间、喷射压力、喷射流量和磨料粒度对加工效果的影响的一般规律.     

不同孔型对气膜冷却效果影响的数值模拟

为了解气膜冷却技术中孔型作用的影响,采用数值模拟方法,在主流速度20 m/s,湍流度6％,主、射流温分别为333 K和293 K的条件下,考察无复合角、流向角为35°时的圆柱孔、收缩-扩散孔和反涡孔进行平板气膜冷却的冷却效果.其中,圆孔孔径12.7mm,长径比3.5,与集气室连接面形式同于其余孔型.模拟过程中,湍流Real-izable k-ε方程,标准壁面函数处理边界,SIMPLEC算法实现压力、速度耦合.结果表明:由于反涡射流抑制了肾型涡的形成并减弱了肾型涡的强度,反涡孔的冷却效果和覆盖区域优于其他两孔型.     

离散涡丝方法模拟矩形射流场的研究

采用三维离散涡方法对不可压矩形射流场进行了数值模拟，结果发现与圆射流不同的是，即使在不加扰动的情况下，封闭涡丝也极不稳定，不再呈现矩形，而是波浪形，并有流向涡产生。矩形涡丝失稳和演变的程度都比圆形涡环的情形更快，本结果对于矩形射流的利用具有指导意义。     

射流噪声抑制的数值方法——共轴射流的研究

由于喷气飞机中发动机产生的气动噪声是飞行时的主要噪音之一,因此射流噪声的研究具有重要的意义。文章结合CFD技术与气动噪声时域理论求解共轴喷管的射流噪声。首先采用雷诺平均N-S方程求解器对射流的三维流场进行了数值模拟。通过数值模拟,得到了共轴喷管马赫数为0.75的流场特性。然后结合lighthill声比拟理论研究了流场产生的气动噪声。结果发现,由于次级流对主流的影响,导致射流流场结构改变,剪切层内的大尺度涡减小,与常规单喷管射流噪声相比共轴射流有所改善,特别是在高频段喷流噪声有明显减小。     

涡流板能量分离特性实验研究

涡流板由多个涡流管集合而成,可以克服单个涡流管制冷量小的缺点．用实验方法研究了人口参数和冷流比对涡流板能量分离特性的影响．实验中以空气为介质分别研究了人口温度、压力及冷流比对涡流板的制冷效应、制热效应、绝热效率的影响规律．研究结果表明,人口温度升高有利于涡流板能量分离;人口压力升高,涡流管制冷、制热效应增加而绝热效率下降;冷流比增加,涡流板制热效应和绝热效率增加,而制冷效应下降．因此,涡流板与单管涡流管具有相同的能量分离特性,为进一步研究涡流板奠定了基础．     

Numerical simulation of 3D viscous flow field of air cooled turbine blades with coolant mixing

To improve thrust and reduce oil consumption of aero-engines, the temperature at turbine inlet is becoming higher and higher, which leads to heavy thermal load of vanes. To efficiently cool the vanes, the mass of coolant with its maximum gas mass flow exceeding to 20% of main stream, has to be increased. In the pres- ent paper, a two-stage turbine with and without coolant mixing was simulated by CFX-TASCflow. Simulation resuits indicate that the flow field structure with coolant is obviously different from that without coolant, and the former has characteristics of lower-speed main flow, reduced mach number, weaker shock intensity and decreased stage efficiency.     

船用压水堆核动力装置采用双恒定运行方案对总体运行性能的影响分析

双恒定运行方案是船用压水堆核动力装置的理想运行方案。在这种运行方案下,当装置稳态功率变化时,冷却剂平均温度与蒸汽压都保持不变,与通常常用的冷却剂平均温度恒定运行方案相比,有效地改善了核动力装置的总体运行性能,特别是在低负荷运行时,可以提高装置在经济性、降低主泵运行噪声、改善二回路系统的设计、运行和控制条件,这对于提高船用核动力装置的运行可靠性和安全性具有实际意义。     

Ignition,flame propagation and extinction in the supersonic mixing layer flow

The supersonic mixing layer flow, consisting of a relatively cold, slow diluted hydrogen stream and a hot, faster air stream, is numerically simulated with detailed transport properties and chemical reaction mechanisms. The evolution of the combustion process in the supersonic reacting mixing layer is observed and unsteady phenomena of ignition, flame propagation and extinction are successfully captured. The ignition usually takes place at the air stream side of braid regions between two vortexes due to much higher temperature of premixed gases. After ignition, the flame propagates towards two vortexes respectively located on the upstream and downstream of the ignition position. The apparent flame speed is 1569.97 m/s, which is much higher than the laminar flame speed, resulting from the effects of expansion, turbulence, vortex stretching and consecutive ignition. After the flame arrives at the former vortex, the flame propagates along the outer region of the vortex in two branches. Then the upper flame branch close to fuel streamside distinguishes gradually due to too fuel-riched premixed mixtures in the front of the flame and the strong cooling effect of the adjacent cool fuel flow, while the lower flame branch continues to propagate in the vortex.     

Electronically Controlling the System of Preheating Intake Air by Flame for Diesel Engine Cold－Start

In order to improve the cold-start performance of heavy duty diesel engine, electronically controlling the preheating of intake air by flame was researched. According to simulation and thermodynamic analysis about the partial working processes of the diesel engine, the amount of heat energy, enough to make the fuel self-ignite at the end of compression process at different temperatures of coolant and intake-air, was calculated. Several HY20 preheating plugs were used to heat up the intake air. Meanwhile, an electronic control system based on 8 bit mi-cro-controller unit (MCS-8031) was designed to automatically control the process of heating intake air. According to the various temperatures of coolant and ambient air, one plug or two plugs can automatically be selected to heat intake air. The demo experiment validated that the total system could operate successfully and achieve the sched-uled function.     

Specific Properties of Air Flow Field Within the Grinding Zone

1 Introduction Grinding is a precision machining process ,whichis widely usedin manufacturingindustry.Today, modernindustrial production depends to a large degree on grinding machines[1 ,2]. Agood case in point is that ceramicmaterial ,one kind of engineering materials ,can be manufactured only by grinding.Toi mprove the manufactur-ing efficiency,one usual wayis toincrease the rotating speed of grinding wheel ,namely,toincreaseits periph-eral velocity. However , not only the temperature of gr…     

同心双涡旋非接触真空吸盘防旋研究

为解决传统单涡旋吸盘由于内部旋转流场的作用引起被吸工件旋转从而导致非接触吸取失效的问题,提出一种同心双涡旋非接触真空吸盘技术方案,其内、外两个涡旋气腔结构同心但气流旋向相反。内涡旋产生真空提供吸力,外涡旋用于平衡内涡旋对工件产生的摩擦转矩。研究该型吸盘工作参数对被吸工件的摩擦转矩及吸力的作用规律,仿真结果表明：同样的供气压力下,外涡旋气流对被吸工件产生的摩擦转矩略大于内涡旋气流,表明可通过适当减小外涡旋腔的供气压力以达到防旋效果;同等供气流量下,双涡旋吸盘的吸力略小于单涡旋吸盘。分析了双涡旋吸盘关键结构参数对吸力的影响规律并进行了正交实验,得到最优结构参数组。加工制作双涡旋吸盘样机并进行了试验研究,结果表明：同等试验条件下,同心双涡旋非接触真空吸盘的吸力与传统的单涡旋吸盘的吸力基本相当,被吸工件所受的摩擦转矩可减小90%左右,很好地抑制了被吸工件的旋转,提高了真空吸取搬运的稳定性和可靠性。     

船用压水堆核动力装置双恒定运行方案下的冷却剂流量调节方案

船用压水堆核动力装置采用双恒定运行方案，蒸汽发生器一次侧冷却剂流量必须随着装置负荷按照一定规律而变化。本文对冷却剂流量调节的几种方案进行分析和比较，指出最为理想的调节方式是采用主泵变频调速。     

Experimental Investigation on Flow and Drying Characteristics of Impinging Stream Drying

Based on the experimental investigation of one-stage semi-circular impinging stream drying, the experiments with the two- stage semi-circular, as well as the vertical and semi-circular combined impinging stream drying were conducted. The variations of system pressure drop, the mean residence time of particles with the mass flow-rate ratio and air velocity ate. were determined. The influences of inlet air temperature, mass now-rate ratio, initial moisture content of particles and air velocity ate. on drying characteristics were also studied. The results indicate that the vertical and semi-circular combined impinging stream drying can make full use of the advantages of both the vertical and semi-circular impinging stream drying. Reasonable mass flow-rate ratio, air velocity, and higher inlet air tem- perature should be used for less energy consumption and cost during drying process.     

Numerical investigation of radial inflow in the impeller rear cavity with and without baffle

In typical small engines, the cooling air for high pressure turbine(HPT) in a gas turbine engine is commonly bled off from the main flow at the tip of the centrifugal impeller. The pressurized air flow is drawn radially inwards through the impeller rear cavity. The centripetal air flow creates a strong vortex because of high inlet tangential velocity, which results in significant pressure losses. This not only restricts the mass flow rate, but also reduces the cooling air pressure for down-stream hot components. The present study is devoted to the numerical modeling of flow in an impeller rear cavity. The simulations are carried out with axisymmetric and 3-D sector models for various inlet swirl ratio β_0(0–0.6), turbulent flow parameter lT(0.028–0.280) with and without baffle. The baffle is a thin plate attached to the stationary wall of the cavity, and is proved to be useful in reducing the pressure loss of centripetal flow in the impeller rear cavity in the current paper. Further flow details in impeller rear cavity with and without baffle are displayed using CFD techniques. The CFD results show that for any specified geometry, the outlet pressure coefficient of impeller rear cavity with or without baffle depends only on the inlet swirl ratio and turbulent flow parameter. Meanwhile, the outlet pressure coefficient of the cavity with baffle is indeed smaller than that of cavity without baffle, especially for the cases with high inlet swirl ratio. The suppression of the effect of centrifugal pumping and the mixing beween the main air which is downstream of the baffle and the recirculating flow of the vortex in the stationary cavity, which are caused by the use of baffle, are the underlying reasons that lead to the reduction of outlet pressure loss.