Damage Mechanism of High Chrome Bricks for Opposed Multi Nozzle Gasifier and Their Improvement

To reveal the damage mechanism of high chrome bricks for opposed multi nozzle gasifier with expanded diameter,the chemical composition and the morphology of a used high chrome brick were researched using XRF,SEM and EDS,and the properties of the high chrome bricks were improved by adding ultra fine alumina,alumina-chrome-iron oxide synthetic material with spinel structure,and chromium metal.The results show that(1)the high chrome brick is seriously damaged by the chemical dissolution of chrome as well as the chemical reactions at the slag/brick interface,the slag penetration and the structural spalling;(2)FeO in the slag reacts with Cr_(2)O_(3)in the brick to form a FeCr_(2)O_(4)layer on the particle surface thus leading to spalling;CaO reacts with SiO_(2)and Al2O3 in the brick forming a metamorphic layer of low melting point materials;due to the different thermal expansion coefficients of the metamorphic layer and the original brick,cracks appear and continue to expand and deepen under multiple temperature and pressure fluctuations thus leading to spalling of brick layer;(3)the improved brick has decreased apparent porosity,increased bulk density and compressive strength,and better thermal shock resistance compared with the original brick;after one cycle of on-site application,the furnace lining surface is smooth and flat with little damage,indicating that the improved high chrome bricks basically meet the working condition requirements of the opposed multi nozzle gasifier with expanded diameter,however,the final effects need to be evaluated in detail after the whole furnace service.

Numerical simulation of the gas-solid two-phase flow inside the multi-channel nozzle for the surface nanocrystallization induced by the ultrasonic particulate peening

Using a gas-solid two-phase model(a discrete phase model),the authors investigated the flow field inside the multi-channel nozzle for surface nanocrystallization(SNC)induced by the ultrasonic particulate peening(USPP).By computation,the velocity fields of both the gas and the solid phases were simulated and the track of the solid phase was analyzed in detail.It can be found that the velocities of the two phases are able to reach an ultrasonic level;meanwhile,the dispersion width of the solid phase at the nozzle exit is less than that of the gas phase.When particle diameters are less than 5 μm,there is a decreasing trend in the dispersion width of the solid phase with an increase in particle diameters.The trend becomes stable as the particle diameters are greater than 5 μm;in the meantime,the distribution of solid particles is near the axis of the jet flow.The optimal standoff distance between the nozzle and the substrate in the process of USPP is about 120 mm.Simulation results can help improve the design of mass-production-oriented multi-channel nozzles for SNC induced by USPP.

The Influences of the Nozzle Throat Length and the Orifice Grooving Degree on Internal Flow Field for a Multi-Entry Fan Nozzle Based on FLUENT

Spray nozzle is a key component in equipment for plant protection and water-saving irrigation. The fan nozzle is a kind of spray nozzle, which is widely used in agriculture and forestry for irrigation and control of diseases, insects, and weeds. In consideration of the increasing velocity of the flow field, when the hydraulic pressure remains unchanged and the flow path becomes narrow, and because the increase of the velocity of spray drops can increase the penetrability of spray drops into the plant canopy, a kind of new fan nozzle with multi entries and simple inner structure was designed and the influences of its structure parameters on the inner flow field were analyzed using FLUENT software. The experimental results showed that the influence of the throat length on the inner flow field of the nozzle was insignificant, while the orifice grooving degree had a significant effect on inner flow field of the nozzle. The larger the grooving degree was, the smaller the pressure and velocity of internal flow field of the nozzle. The nozzle throat length had little influence on the velocity change of internal flow field. Positive correlation was shown between throat length and flow field velocity.

Multi-Schlieren CT Measurements of Supersonic Microjets from Circular and Square Micro Nozzles

Instantaneous three-dimensional (3D) density distributions of a shock-cell structure of perfectly and imperfectly expanded supersonic microjets escaping into an ambient space are measured. For the 3D observation of supersonic microjets, non-scanning 3D computerized tomography (CT) technique using a 20-directional quantitative schlieren optical system with flashlight source is employed for simultaneous schlieren photography. The 3D density distributions data of the microjets are obtained by 3D-CT reconstruction of the projection’s images using maximum likelihood-expectation maximization. Axisymmetric convergent-divergent (Laval) circular and square micro nozzles with operating nozzle pressure ratio 5.0, 4.5, 4.0, 3.67, and 3.5 have been studied. This study examines perfectly expanded, overexpanded, and underexpanded supersonic microjets issued from micro nozzles with fully expanded jet Mach numbers Mj ranging from 1.47 - 1.71, where the design Mach number is Md = 1.5. A complex phenomenon for free square microjets called axis switching is clearly observed with two types “upright” and “diagonal” of “cross-shaped”. The initial axis-switching is 45° within the first shock-cell range. In addition, from the symmetry and diagonal views of square microjets for the first shock-cells, two different patterns of shock waves are viewed. The shock-cell spacing and supersonic core length for all nozzle pressure ratios are investigated and reported.

Cold-state Experimental Study on Flow Characteristics of Multi-nozzle in Natural Gas Reburning Burner

Based on the prototypes of a 130 t/h boiler, constant proportional cold-state test bench is established, flow characteristics of multi-nozzle in natural gas reburning burner and its influence on the covering effect for the upflow in the furnace are researched. Numerical simulations of this process are also made with standard ?turbulence model. The results show that air flow fullness in furnace is better in the case of the reburning zone with 8 nozzles compared to 4 nozzles and also coverage effect of the reburning flow for the updraft gas in the furnace is better. In the condition each nozzle airflow velocity is constant, the effect of reburning flow on coverage of up-secondary air is best when the incident angle for four corners is 14.17?, while Center of the furnace wall is 84.57. And while the best incident angle is invariable, the effect of reburning flow on coverage of up-secondary air is best when the speed of reburning gas in the corners of furnace is 51 m/s, the same to the center of the furnace wall’s.

Effect of Swirl Preset Vorticity on Combustion Performance of Lobe Nozzle Combustor Chamber

To improve the combustor performance of multi-point injection combustion,lobe nozzle design was applied to the aero-engine model combustor,by presetting the swirl through a certain twisted angle of the edge of the lobe outlet.Numerical simulation in combination with modelling test is used in this paper.The effects of swirl vorticity presetting onto the vortex structure,the characteristics of combustion temperature field,the combustor exit temperature field quality,the combustion efficiency,and the NOx emissions of multi-point injection combustion chamber are investigated.Compared with the conventional vortex flow at the lobe outlet edge,the results of numerical simulation and water modelling test of the swirl vorticity presetting show that the swirl presetting can efficiently enhance the range and intensity of the lobe-induced vorticities.Besides,it can improve the uniformity of the combustion temperature in the combustor chamber,together with the reduced emissions of the pollutant NOx.Moreover,compared with the conventional lobe nozzle chamber,the swirl vortex presetting can effectively improve its combustion performance.The flow simulation test results demonstrate the fluid vortex structure in the combustion chamber and validate the simulation results.

多喷头纺丝装置的仿真与设计

针对静电纺丝多喷头间电场强度分布不均匀所导致的纺丝液射流运动轨迹不稳定、纺丝纤维分布较为分散等边缘效应问题,采用COMSOL Multiphysics软件,通过深入研究多喷头静电纺丝的纺丝电压、喷头间的横向间距和纵向间距对多喷头电场强度分布均匀性的影响程度,给出削弱多喷头边缘效应的喷头最优空间位置关系。结果表明:在三喷头仿真实验中,增大喷头间的横向间距,3个喷头的电场强度随着纵向间距的减小而逐渐趋于一致;当横向间距为5.0 cm、纵向间距为0.5 cm时,边缘效应能够得到有效缓解,且该间距更有利于多喷头的结构设计;五喷头、九喷头静电纺丝装置在保持横向间距为5.0 cm不变的情况下,纵向间距为0.5 cm时的电场强度分布相对于零点位置更加均匀,且九喷头的效果最好。通过实验验证,九喷头结构具有纺丝面积大、效率高和纺丝过程稳定等优点,研究结果可为纺丝装置的多喷头结构研究与设计提供借鉴。

改进7N喷头阻隔CO扩散有效性的模拟研究

为弥补常规组合式喷头存在的挡烟空隙不足,在普通7N喷头的基础上改进,设计出一种侧喷式7N喷头,并开展了数值模拟研究。通过对比下游截面处CO总质量通量、流场分布以及温度的变化情况,验证了改进喷头挡烟的有效性。在此基础上,分析了改进喷头在不同火源功率、流量、粒径下的作用效果。结果表明,普通喷头形成的雾幕能够有效降低通道温度,但并不能阻隔CO的扩散。在同样条件下,改进后的雾幕能够有效抑制CO蔓延,降温能力也有所提高,且其作用效果随喷头流量的增大更加显著。在流量为11.42 L/min时,下游CO质量通量及最高温度较改进前分别降低了71.64%、30.05%;即使火源功率增大至5 MW,改进后的雾幕仍能有效限制CO扩散;总体来看,粒径对CO的阻挡影响并不明显,对2 MW火灾的降温效果也在粒径200 m时达到最佳。

花瓣状多尖端静电纺丝喷头的电场模拟及优化

针对目前多针头静电纺丝易堵塞、针头之间存在边缘效应和无针头静电纺丝供液易挥发、泰勒锥位置不可控等问题,提出一种花瓣状多尖端喷头静电纺丝方法。喷头为半封闭式结构,上半部分为圆柱直管多流道结构,下半部分为花瓣状流道扩张结构,每层的花瓣之间的间距为4 mm,能够在花瓣尖端高电场诱导作用下激发多股射流;利用COMSOL有限元分析软件对下半部分花瓣状流道扩张结构的各个参数电场强度进行模拟,研究喷头下端花瓣数量、花瓣长度和花瓣排布方式对电场均匀性的影响。结果表明:当静电纺丝喷头花瓣数量为4对(8个)、花瓣内层长度为21 mm、外层长度为20 mm、接收距离为200 mm、电压为30 kV时,电场强度平均值为5.441×10^(6) V/m,变异系数(CV)值为5.58%,表明该静电纺丝喷头可激发较高的电场强度且分布均匀;最后采用静电纺丝设备进行纺丝实验,验证了该新型花瓣状多尖端静电纺丝喷头在静电纺丝过程中能够降低边缘效应,减小能耗,射流多且稳定可控,可进行规模化静电纺丝。

静电纺聚酰胺6/聚苯乙烯复合纳米纤维膜制备及其空气过滤性能

针对空气过滤纤维材料的过滤效率、阻力和使用寿命难以平衡的问题,采用多喷头静电纺丝技术,制备了不同直径、形貌纤维及不同纤维沉积顺序的聚酰胺6/聚苯乙烯(PA6/PS)复合纳米纤维膜,测试了复合膜的平均孔径及孔隙率,建立了纤维结构与过滤效率及阻力的构效关系;结合扫描电镜表征探讨了不同形貌、直径纤维的叠加次序对过滤寿命及细颗粒物沉积行为的影响,系统研究了过滤风速、细颗粒物尺寸对过滤性能的影响。结果表明:在5.33 cm/s的风速下,以多喷头静电纺丝方式制备的PA6/PS复合膜具有更好的抵抗风速变化的能力,在长期使用中阻力增加较缓慢,其具有93.13%的过滤效率,30.67 Pa的过滤阻力和0.0889 Pa-1的品质因子,综合过滤性能优于同等条件下H10等级(过滤效率>90%)的商业玻璃纤维过滤膜。

燃料分级对贫预混多喷嘴燃烧器火焰动态响应特性影响的实验研究

贫预混多喷嘴燃料分级技术可以有效降低局部热负荷,从而降低NOx排放并拓宽工况范围,是现代重型燃气轮机低排放燃烧室的主要燃烧方式。本文开展了燃料分级及当量比变化对贫预混多喷嘴燃烧火焰动态响应的影响研究。利用扬声器产生火焰的受迫振荡,利用压力脉动传感器与光电倍增管完成了多喷嘴火焰响应特性的试验分析。试验表明,燃烧室内压力波动与热释放率波动随扰动频率同步变化。当量比低于0.53时,多喷嘴火焰传递函数呈现单峰的特征。当量比大于0.64时,多喷嘴火焰传递函数呈现双峰特征,且火焰响应增强。延迟时间τ随着当量比的增大而减小。燃料分级将使得火焰动态响应特征频率发生偏移。增加喷嘴数量使得火焰传递函数幅值上升,火焰响应增强,峰值频率增大,延迟时间偏短。对于采用多喷嘴燃料分级技术的燃烧室,负荷上升将导致火焰趋于不稳定。

多喷嘴挡板单级电液伺服阀数学模型及特性分析

多喷嘴挡板单级电液伺服阀是飞机辅助动力装置的重要部件之一,起到精确控制燃油流量的作用。针对其力矩马达初始气隙非对称、单侧四喷嘴等独特的结构形式,分析了工作机理,建立了整阀的数学模型,并通过MATLAB/Simulink对数学模型进行了仿真研究,得到了各组件以及整阀的输出特性。其中,力矩马达气隙初始值非对称产生的电磁力矩可以平衡一部分喷嘴液压力产生的力矩,考虑喷嘴腔的压力损失与不考虑时二者误差最大为11.4%。同时开展了多喷嘴阀实验研究,对比数学模型与实验得到的整阀流量特性曲线,二者基本一致,验证了所建立的数学模型的准确性,为多喷嘴挡板电液伺服阀特性分析奠定了基础。

CMC S弯喷管材料-结构多尺度优化设计研究

S弯喷管作为大尺寸薄壁结构,在多场耦合作用下有着复杂的整体和局部刚度特性。本文针对S弯喷管变形特征,提出一种基于陶瓷基复合材料(CMC)的S弯喷管连续筋条加强结构,可以有效抑制S弯喷管的整体变形和局部变形。与GH4169合金相比,CMC材料可以降低S弯喷管45.31%的变形量,同时减重62.77%,在此基础上,采用连续筋条加强结构可以进一步降低CMC S弯喷管43.15%的变形量。基于代理模型和差分进化算法,以CMC材料筋条加强S弯喷管的结构质量为目标,以CMC材料细观编织结构中的经/纬纱比例以及喷管宏观结构中的分区域壁厚和加强筋尺寸为优化变量,开展了材料-结构多尺度优化,在相同的刚度指标要求下进一步优化减重26.21%。

轴对称矢量喷管运动学建模及运动轨迹分析

轴对称矢量喷管为复杂的空间多链路机构,是推力矢量技术的核心。为研究其运动规律,将空间机构位置分析法、解析几何法和环路矢量法相结合,建立了轴对称矢量喷管的空间运动学模型。利用数值仿真实现了其运动姿态的仿真,并通过与ADAMS仿真结果对比,验证了该模型的正确性,进而获得轴对称矢量喷管在不同驱动方式下的位姿以及喉口和喷口的面积变化规律。结果表明:喉口状态和喷管运动状态对喷管面积比均有影响,面积比随着A9作动筒的同步伸长呈明显单调递增状态;A9作动筒异步驱动时,喷管面积比变化较小,喷口矢量偏转角角速度与作动筒运动速度呈比例关系,截面形状由圆形逐渐变为空间上扭曲的椭圆形;拉杆尺寸对喷管机构的面积比变化范围有明显影响,拉杆每增大(或减小)1 mm,面积比变化区间整体上移(或下移)0.025。仿真结果有助于了解喷管的运动规律,可为喷管的参数化分析及优化设计提供理论依据。

基于Fluent的多级串联喷嘴液气射流泵的抽气性能研究

为提高液气射流泵的抽气性能,在其主喷嘴后设置了多级串联喷嘴,通过Fluent软件对常规液气射流泵和多级串联喷嘴液气射流泵内气液两相流体运动情况进行了数值模拟,对比分析了相同工况下两种类型液气射流泵的抽气性能、压力场分布、速度场分布和气相体积分数分布。结果表明:在工作流体进口压力(表压)为0.3 MPa、0.35 MPa和0.4 MPa下,多级串联喷嘴液气射流泵的抽气性能较常规液气射流泵分别提高了18.1%、13.4%和20%,多级串联喷嘴结构有利于气液两相流体的混合和动量交换。研究结果对液气射流泵的优化设计和抽气性能提高具有一定的参考意义。

一种喷口控制的多目标约束设计方法

为克服试凑法在控制回路参数优化中的局限性,针对涡扇发动机在加力状态易出现喷口摆动的不协调现象,考虑喷口双环控制结构工作特点,采用按需正向设计策略,按照控制系统时域、频域性能指标设计要求,制定兼顾频域、时域性能要求的内、外环协调控制的设计目标准则,提出一种喷口控制的多目标约束的差分进化内外环控制参数自整定优化设计方法,在双转子涡扇发动机非线性模型上进行闭环控制系统仿真验证。结果表明:在飞行高度从0增加到10 km、飞行马赫数从0加速到0.9的起飞和爬升状态进入加力过程以及平飞中保持飞行马赫数不变的关断加力过程中,发动机未出现喷口摆动等现象,涡轮落压比最大相对误差不大于1.5%,喷口闭环控制系统具有期望的伺服跟踪和抗飞行条件变化干扰能力。

基于Fluent对水平压裂喷嘴结构的参数设计

页岩油气是一种通过水力压裂和水平井技术开采的非常规能源资源。由于页岩储层的低渗透性和低孔隙度,产能相对较低。为解决页岩油气开采的技术难题,实现更有效、可持续的页岩油气开采方式,基于AnsysFluent对喷嘴结构及其参数进行优化,建立了喷嘴的流体力学模型,并绘制了等速核轴向速度变化曲线、喷嘴出口截面速度变化曲线、流场速度云图等,并对不同结构及参数的喷嘴的等速核长度及速度大小进行比较,从而根据数值模拟及仿真结果选择最优结构和参数。研究表明,在倒角、圆角、渐变、三段式结构中,同等压力条件下,渐变式和圆角结构等速核最长;同等流量条件下,倒角结构等速核速度最大,三段式结构等速核最长,圆角结构其次。结合以上仿真结果,设计一种倒角、圆角结合的喷嘴结构,并以倒角(圆锥段)角度、圆柱段长度为参数研究其对射流速度及等速核长度的影响,综合考虑,得到12种三段式结构中最优的结构,并总结出各参数对射流的影响。

基于轴芯材料可切换的同轴3D打印技术及应用研究

目前,主流的直书写3D打印多材料打印方法是通过设计多个入口挤入汇合到单个出口挤出的喷头,材料按照需要有机地结合在一起,实现不同性能的组合。但是,多材料增材制造需要各材料之间具有优异的黏合强度,同时需要材料参数满足高黏度和剪切变稀的特性以符合3D打印的各项要求。为了实现多材料的连续稳定性打印,通过设计一种轴芯材料具有快速切换功能的同轴挤出3D打印喷头及其打印系统,研究多材料同轴打印原理及打印实验。CCM3D喷头允许不同流变特性的轴芯材料稳定地选择性挤出,实现多材料同轴制造。通过生成多材料G代码进行打印,展示了轴芯两种不同黏性材料之间的快速切换以及2D图像的打印,利用同轴多材料的打印优势,将不同弹性模量的硅胶选择性嵌入同轴线条轴芯,展示了其打印3D模型的能力。

水力喷射自钻进多孔喷嘴打击力特性研究

为了探讨水射流自钻进喷嘴射流旋转打击力特性,确定了喷嘴结构参数,建立了水射流旋转打击力测试系统,开展了在不同喷嘴直径、射流角度、旋转速度、射流靶距和射流压力条件下打击力试验,分析了打击力随各影响因素的变化规律。试验结果表明:打击力随喷嘴直径增大而增大,随射流角度增大而减小;在不同射流压力下,存在最佳旋转速度200 r/min,此时射流打击力为最大值;6 mm靶距附近为射流充分发展阶段,该区间射流打击力值最高;打击力与射流压力之间呈正相关关系,当压力超过30 MPa时打击力增长趋势明显降低。最后讨论了射流打击力最大值组合参数,为水射流自钻进破岩工作参数优选提供参考。

自进式喷嘴仿真分析

多分支小井眼完井技术可以提高低渗油田的开发效率,最大化发挥油田的经济效益。自进式喷嘴作为多分支完井的核心部件,影响着多分支管线的破岩效率和钻进深度。文中建立了自进式喷嘴的三维模型,通过流体仿真软件,分析了喷嘴在前后喷孔不同配置情况下的破岩力及推进力,优选出推进力大、破岩力强的喷嘴配置,为提高多分支管线的破岩效率和钻进深度提供了理论基础。