旋流数对小限制率旋流喷雾及火焰特性的影响

分布式贫油直喷（Distributed Lean Direct Injection,DLDI）燃烧室是国外多点贫油直喷（MLDI）燃烧室的实用发展形式。本文对DLDI燃烧室的主燃级单元LDI开展研究,主要关注外旋流器旋流数（Sn）从0.65降低到0.33对流场、喷雾和火焰结构的影响。利用FLUENT软件、采用雷诺平均方程（RANS）对时均流场进行求解;利用离散相模型（Discrete Phase Model）对喷雾散布进行模拟;利用Mie散射和激光粒度测量仪对喷雾散布和SMD（Sauter Mean Diameter）进行测量,并对仿真结果进行验证;利用高速摄像机拍摄火焰结构。研究结果显示Sn变化直接改变流场结构：随着Sn的减小,外旋流射流对内旋流射流的压制逐渐变强,内旋流射流的张角和中心回流区尺寸都逐渐缩小;尤其在Sn为0.33时,角涡回流区演化成壁面回流区。流场变化影响液雾散布：Sn在0.38~0.65区间时,喷雾核心主要由内旋流射流输运,喷雾张角由内旋流射特性决定;当Sn为0.33时,喷雾核心会在自身惯性下射入外旋流射流,在外旋流射流以及壁面回流区的作用下均匀散布。喷雾散布结果表明喷雾核心射入外旋流射流时更有利于液雾的散布。火焰结构的研究结果显示在小限制率条件下,Sn为0.33时,中心回流区回流量不足、无法稳定火焰,此时形成的壁面回流区创造了新的稳火点来帮助稳定火焰。     

Spray characteristics of jet–swirl nozzles for thrust chamber injector

Thrust chamber injector is very critical component since that small differences in its design can result in dramatically different performance. This paper presents a preliminary investigation of a mono-propellant jet–swirl nozzle for thrust chamber using the existing commercial nozzle made of brass with little modification. The performance of two types of spray pattern, i.e. hollow cone and solid cone were investigated under cold flow test. Two solid cone injectors were studied at various purely axial orifice diameter with all other parameters remaining constant. This investigation reveals that decrease in the breakup length increased the spray angle. Higher injection pressure leads to shorter breakup length and higher value of discharge coefficient, except for hollow cone nozzle which shows mild fluctuating trend. Experimental data also tells that solid cone nozzle with diameter ratio 0.14 has the highest average discharge coefficient (0.60), followed by hollow cone nozzle (0.25). Solid cone nozzle with diameter ratio of 0.1 has an average discharge coefficient of 0.21.     

进气道旋流模拟及测量的实验研究

进气道出口旋流是影响进气道/发动机相容性中的一个重要因素。为在地面试验中评价进气道旋流对发动机稳定性的影响,设计了叶片式旋流发生器,并在风洞中进行了整体涡旋流、对涡旋流两种基本旋流流场的模拟,实验中利用在固定马赫数下校准的五孔探针测量了所模拟的旋流场。风洞实验结果表明,按照不同布局方式来安装叶片,可以得到不同形式的旋流场;旋流发生器叶片攻角对旋流强弱的影响较为明显;旋流的诱导速度对旋流中心位置有很大的影响。     

带旋流杯的模型回流燃烧室主燃孔射流研究

实验研究了带轴径向旋流杯、主燃孔和冷却气流的模型回流燃烧室在工作压力为300 kPa, 燃烧室压力损失为2.5%时主燃孔射流的特点以及其对燃烧室流场的影响.结果表明, 回流式燃烧室内外壁主燃孔射流进气方向与顺流式燃烧室不同, 即内壁主燃孔射流向流动方向下游倾斜, 外壁主燃孔射流向流动方向上游倾斜;主燃孔射流穿透深度很大, 几乎能穿透到对面火焰筒壁;中心回流区长度明显缩短, 其长度L与旋流杯出口直径D的比值(L/D)约为0.5, 而常规的顺流式燃烧室的L/D约为1.3.      

横喷射流与空气混合增强的试验研究

提出利用垂直横喷射流引入流向旋涡来增强氢和空气的混合。射流中心剖面速度分布和射流轴线最大速度衰减的五孔探针测量结果表明,单孔射流与来流空气的动量比越大,混合越迅速。二维射流的混合要比三维射流差的多。单排多孔射流在一定的孔面积和流量比下,协调孔距、通道高度和射流动量比的关系,就可获得射流与来流空气的最佳混合,然后据此确定喷孔直径和数目。首次引入三维垂直射流旋涡穿透深度的概念,这比最大速度穿透深度更具实际意义。     

空间双组元发动机离心式喷注器的喷注流场诊断技术研究

对空间双组元发动机核心部件喷注器的喷雾流场可视化诊断技术开展了研究,有效识别了传统分析手段难以发现的雾化场缺陷,对发动机工作特性进行早期诊断,实现故障预防和设计优化.离心式喷注器的雾化喷注流场包含了大量的数据信息,可以通过高速摄影和图像分析进行数据挖掘分析.通过均值图像和余弦相似性计算对喷注流场的空间分布结构进行诊断,...     

基于体积力模型的大S弯进气道与风扇耦合计算研究

为理解超紧凑大S弯进气道与风扇的耦合效应,基于体积力模拟方法开展了一体化计算研究。研究的进气道长径比为2.5,使用Rotor 67进行耦合分析,体积力模型与冻结转子计算得到的总压比、总温比和等熵效率分别相差4.49%,0.26%和2.38%。流场分析表明,风扇对入口段流场影响较为明显,主要体现为畸变区的顺向偏转与微弱衰减;进气道出口畸变经过风扇叶片后得到改善,大低压区和反向旋流基本消失;而流体在叶片的前后缘旋流角与轴向速度的综合改变量越大,风扇对气流做功越多。总的来说,超紧凑大S弯进气道与风扇之间耦合比较明显,需要在设计时进行详细的考察。     

Precessing motion in stratified radial swirl flow

Vortex/flame interaction is an important mechanism for unsteady combustion in a swirl combustion system. Technology of low emission stirred swirl(Te LESS), which is characterized with stratified swirl flow, has been developed in Beihang University to reduce NOXemission. However,large-scale flow structure would be induced in strong swirl flow. Experiments and computational fluid dynamics(CFD) simulation were carried out to investigate the unsteady flow feature and its mechanism in Te LESS combustor. Hotwire was firstly applied to testing the unsteady flow feature and a distinct mode with 2244 Hz oscillation frequency occurred at the pilot swirl outlet.The flow mode amplitude decayed convectively. Large eddy simulation(LES) was then applied to predicting this flow mode and know about its mechanism. The deviation of mode prediction compared with hotwire test was 0.8%. The spiral isobaric structure in pilot flow passage indicates that precessing vortex core(PVC) existed. The velocity spectrum and phase lag analysis suggest that the periodic movement at the pilot outlet was dominated by precessing movement. Negative tangential momentum gradient reflects that the swirl flow was unstable. Another phenomenon was found out that the PVC movement was intermittently rotated along the symmetric axis.     

采用碟型砂轮的圆锥面刃磨机原理设计——非直线主刃刃磨

从圆锥面刃磨原理出发，推导了一般主刃的钻头结构参数的计算公式，研究了刃磨参数对钻头结构参数的影响规律。通过具体实例，介绍了碟型砂轮刃磨原理与设计方法，同时，也为实现钻头刃磨提供了调整使用方法。研究结果表明，合理选择蝶型砂轮，可以实现大范围钻头的锥面刃磨，适当调整刃磨参数可以基本满足大部分给定设计参数钻头的刃磨，对于大后角、大锋角、小横刃斜角参数组合的钻头刃磨完成较大。     

A new approach to solar wind monitoring

The monitoring of solar wind parameters is a key problem of the space weather program. We are presenting a new solution of plasma parameter determination suitable for small and fast solar wind monitors. The first version will be launched during the SPECTR-R project into a highly elongated orbit with apogee ∼350,000 km. The method is based on simultaneous measurements of the total ion flux and ion integral energy spectrum by six identical Faraday cups. Three of them are dedicated to determination of the ion flow direction, the other three (equipped with control grids supplied by a retarding potential) are used for determination of the density, temperature, and speed of the plasma flow. The version under development is primarily designed for the measurements in the solar wind and tail magnetosheath, thus for velocities range from 270 to 750 km/s, temperatures from 1 to 30 eV, and densities up to 200 cm⁻³. However, the instrument design can be simply modified for measurements in other regions with a substantial portion of low-energy plasma as a subsolar magnetosheath, cusp or low-latitude boundary layer. Testing of the engineering model shows that the proposed method can provide reliable plasma parameters with a high time resolution (up to 8 Hz). The paper presents not only the method and its technical realization but it documents all advantages and peculiarities of the suggested approach.