旋风分离器流场的数值计算方法研究

利用计算流体力学软件FLUENT,分别采用k-ε标准模型、RNGk-ε模型和RSM模型湍流模型及不同离散方式对旋风分离器的流场进行了数值模拟研究.通过模拟结果与前人实测结果的对比,确定出了适合旋风分离器的数值计算方法.结果表明:湍流模型采用各向异性的RSM模型,离散方式采用对流项的QUICK格式和压力梯度项的PRESTO格式,才能获得合理的流场模拟结果.该结论为旋风分离器流场的数值模拟及进一步的结构优化设计提供了参考依据.     

五级旋风预热器冷模单体流场数值研究

采用雷诺应力(RSM)湍流模型对五级旋风预热器冷模单体流场进行了数值模拟，并同冷模测试结果进行了比较，取得了较好的吻合性。涡壳采用完全非结构网格，锥筒采用结构网格，有限体积法化湍流运动方程为差分方程．差分格式采用一阶迎风，压力速度耦合采用经典的SIMPLE算法数值求解湍流运动方程组，并在求解过程中采用网格自适应技术。通过对模拟结果分析，得到了旋风筒流场的基本特征。     

等离子点火器三维燃烧流场的大涡模拟

针对等离子点火器的三维燃烧流场进行了大涡模拟．对亚格子项采用Smagorinsky-Lilly模式,湍流燃烧采用涡耗散模型,压力-速度耦合采用SIMPLE算法,空间离散采用中心差分格式,时间离散采用二阶精度的隐式差分格式．得到了燃烧反应流特性参数的分布、湍流燃烧的瞬态发展变化过程以及在拟序结果影响下燃烧的特征．大涡模拟结果表明,复杂的漩涡结构与化学反应的相互作用控制和强化了燃烧过程;在燃烧的充分发展阶段,大涡模拟能更好地反映流场的各项异性和合理的湍流统计物理量的分布,描述了湍流拟序结构对湍流燃烧的影响。     

外旋32型刹克龙内流场的数值模拟

应用PHOENICS程序，采用三维贴体网格，Chen-Kim湍流模型对外旋32型刹克龙内气相流场进行了三维数值模拟．数值模拟结果与实验数据基本相符，对比发现Chen-Kim模型较适合于模拟涡旋流动，可以用来进行旋风分离器的流场模拟．     

圆形喷嘴射流特性模拟方法优化选择

为提高圆形喷嘴射流特性数值模拟研究的准确性、可靠性,分别采用标准k-ε、RNG k-ε、SST k-ω、标准k-ω等4种湍流模型、3种网格划分方案及2种控制方程离散格式对圆形喷嘴射流流场特性进行数值模拟.研究结果表明:与标准k-ε、SST k-ω、标准k-ω三种湍流模型相比,RNG k-ε更能真实地反映圆形喷嘴射流流场特性;在网格划分方案的比较中,方案1所得的平均扭曲率最小,为0.187;对QUICK和二阶迎风格式两种控制方程离散格式的对比发现,二阶迎风格式所得到的轴向速度分布模拟结果更接近实验值.     

矩形方腔湍流自然对流数值模拟研究

利用Lam—Bremhorst低雷诺数湍流模型,对流项差分格式采用QUICK格式,结合非稳态计算方法,对矩形方腔自然对流问题进行了数值模拟研完。计算结果表明：随着时间的推进,流场逐渐稳定,最后趋于定常;将最终稳定的速度场与实验和大涡模拟结果进行比较,发现数值模拟能准确地预测出速度场、温度场以及湍动能场。     

凹腔超声速燃烧室燃烧流场数值模拟

对带凹腔结构的燃烧室二维甲烷燃烧流场进行数值模拟,采用迎风三阶精度MUSCL格式求解二维含组分守恒N-S方程,湍流模型采用剪切修正的RNG κ-ε湍流模型,分别分析了凹腔不同长深比和导流槽结构对燃料燃烧的影响．对喷甲烷燃烧工况进行了计算研究,结果表明：凹腔可以提高燃烧效率,却使总压恢复系数降低;凹腔的长深比越大,燃烧效率越高,总压恢复系数越低;导流槽可以在总压恢复系数较高的情况下进一步提高燃烧效率．     

动力喷流效应混合方法数值模拟研究

从动力喷流效应精细化模拟需求出发,在k-ω SST湍流模型基础上建立了IDDES混合方法,采用了有限体积五阶WENO格式提高空间离散格式精度,开展了动力喷流效应混合方法数值模拟分析及应用研究。基于自由发展喷管流动和ARN2喷管算例,开展了动力喷流效应混合方法数值模拟验证分析,结果表明增加网格密度和提高空间离散格式可有效改善喷流速度分布预测结果,缩短喷管出口下游非物理流动稳定状态,瞬态流场结构更加清晰合理,湍流强度预测更加准确。在此基础上,针对较为实际的涡扇发动机模型,完成了动力喷流效应混合方法数值模拟分析,得到了内、外涵喷流和外界气流的相互干扰及掺混特征,得到了三维湍流结构特征。     

外旋32型刹克龙内流场的数值模拟

应用PHOENICS程序,采用三维贴体网格,Chen-Kim湍流模型对外旋32型刹克龙内气相流场进行了三维数值模拟.数值模拟结果与实验数据基本相符,对比发现Chen-Kim模型较适合于模拟涡旋流动,可以用来进行旋风分离器的流场模拟.     

气-气混合器的三维流场数值模拟

应用RNG的k-ε双方程湍流模型,采用四面体和六面体混合网格,利用CFD技术对气体喷射流混合器内的三维不可压缩湍流流场进行了数值模拟,得到混合器内流场、湍动能、压降及混合浓度场的变化．数值计算表明混合相对均匀、压力降可满足工艺要求．     

Improvement and application of wall function boundary condition for high-speed compressible flows

In order to develop a wall function boundary condition for high-speed flows so as to reduce the grid-dependence of the simulation for the skin friction and heat flux,a research was performed to improve the compressible wall function boundary condition proposed by Nichols.Values of parameters in the velocity law-of-the-wall were revised according to numerical experiments and the expression of temperature law-of-the-wall was modified based on theoretical analysis and numerical simulation.Besides,the formula of the heat conduction term in near-wall region was derived so that the coupling between the wall function boundary condition and CFD code was realized more accurately.Whereafter,the application study of the modified wall function was carried out.The numerical case of supersonic turbulent boundary layer on a flat plate illustrated that the modified wall function produces reasonable results of skin friction and heat flux,and profiles of velocity,temperature and turbulent eddy viscosity for coarse grids with the initial wall spacing of y+<400,and that the modifications to the original wall function can obviously improve the simulation precision.As for the application of separation flows,it was found from the numerical cases of supersonic cavity flow and hypersonic axisymmetric compression corner that the compressible velocity law-of-the-wall originally established based on the fully-developed attached turbulent boundary layer approximately holds in the near-wall region inside the separation flows,which ensures that reliable skin friction and heat flux can be given by the wall function inside the separation flows,while for the region near separation and reattachment points,the wall function gives results with a relatively large error,because the velocity law-of-the-wall used in the wall function takes on obvious deviation from the real velocity profiles near the separation and reattachment points.     

Characteristics of supersonic flow in new type externally pressurized spherical air bearings

In order to predict accurately the characteristics of supersonic flow in new type externally pressurized spherical air bearings under large bearing clearance and high air supply pressure, which could decrease their load carrying capacity and stability, a CFD-based analysis was introduced to solve the three-dimensional turbulent complete compressible air flow governing equations. The realizable κ-ɛ model was used as a turbulent closure. The supersonic flow field near air inlets was analyzed. The flow structures illustrate that the interaction exists between shock waves and boundary layer, and the flow separation is formed at the lower corner and the lower wall around the point of a maximum velocity. The numerical results show that the conversion from supersonic flow to subsonic flow in spherical air bearing occurs through a shock region (pseudo-shock), and the viscous boundary layer results in the flow separation and reverse flow near the shock. The calculation results basically agree with the corresponding experimental data.     

Detached-eddy simulation of supersonic turbulent flow over rearward facing step

Detailed formulation of the detached-eddy simulation(DES)based on shear stress transport model(SST)was deduced.Based on finite volume method,detached-eddy simulation of supersonic turbulent flow over rearward facing step was conducted.Multi-block structured non-conform grid was designed.The obtained distribution of wall pressure coefficient along the downstream of the step was in good agreement with experiment.The structure of supersonic flow over rearward facing step is complicated and contains boundary layer-shock interaction,shock-shock interaction and secondary flow separation.The predictions of the corner pressure and location of the reattachment shock are more exact than the Reynolds-averaged method.Results show that detached-eddy simulation can simulate the supersonic separated flows exactly and has advantages over Reynolds-averaged method.The partition of the detached-eddy simulation can be easily achieved by using multi-block non-conform grid,which reduces the requirement of the computational resources as well.     

循环流化床烟气脱硫塔进口流场模拟及优化

为了改进循环流化床脱硫塔因下部装有的弯管加文丘里管式入口结构所造成的底部区域不均匀气流场,采用RNGκ-ε湍流模型对脱硫塔的气流场进行了模拟计算,讨论了这种进口结构对脱硫塔流场的影响机理,并对该进口结构进行了优化.结果表明:RNGκ-ε模型对于该流场具有较好的模拟效果,在弯管和文丘里管综合作用下,脱硫塔内中下部的气流场分布不均,而返料口对脱硫塔的气流场影响很小.通过对比3种入口结构的优化方式,发现采用改进导流叶片的方式优化效果较好,可成功均布脱硫塔气流场,造成的床层压损也很小.     

汽轮机叶片间流体流动的模拟研究

对超音速汽轮机的叶片间可压缩流体的流动情况进行了模拟研究。在对Giel等人的实验研究结果进行分析的基础上,将转子设计为流向转角为136°和轴向弦长为12.7 cm。通过Fluent软件对各种模型在湍流条件下反射边界情况(RBC)及非反射边界情况(NRBC)进行了二维数值模拟。研究结果对超音速汽轮机的优化设计提供了参考。     

三种湍流模型模拟能力的对比

采用中心有限体积，Runge-Kutta方法显式求解三维Reynolds平均Navier-Stokes方程，使用三种湍流模型数值模拟跨声速及超声速流动。着重介绍半方程J－K模型的两个改进版本：J－K90A模型和J－K92模型，该模型对分离流动有较好的模型能力。J－K模型92年版本具有更好的模拟大攻角，大分离流动的能力，它能较准确地模拟背风面涡的结构与强度，同时能更好地模拟壁面压力分布，当流动存在较强激波时，平衡态的Baldwin-Lomax模型模拟的激波位置明显地靠后。对于附体或中等分离的流动，三种湍流模型都能得到与实验结果吻合良好的结果。     

通用风力机翼型气动特性数值模拟

针对某翼型扰流流动,建立了二维可压缩湍流模型,利用商业软件FLUENT对翼型不同来流攻角下的气动特性进行了相应的数值模拟计算.湍流黏度采用基于RANS的Spalart-A llm aras湍流模型处理,得出了雷诺数在3.2×106时,某翼型的升力系数、阻力系数和压力分布随来流攻角的变化关系,并与同类翼型实验数据进行对比.结果显示:该翼型与修型前的翼型相比,具有较高的升力系数和升阻比,失速性能更好.     

入口参数对双组分混合物自发凝结流动的影响

为了解入口参数对喷管内双组分混合物自发凝结流动特性参数的影响并为超音速分离管的工业应用提供必要的操作参考,建立了双组分混合物自发凝结流动数值模型,对双组分混合物的不平衡凝结流动进行了数值模拟,给出了沿喷管轴向的相关参数分布,模拟结果与相关文献实验结果基本一致.利用上述数值模型研究了不同入口参数对双组分混合物自发凝结的影响,发现对于一定膨胀率和长度的喷管来说,入口压力越低或入口温度越高或入口过饱和度越高,最终的液相质量分数越高.在今后的工业应用时,可以通过适当调节超音速分离管入口处的压力、温度及过饱和度,以实现较好的分离效果.     

应用随机轨道模型研究湍流扩散对气液交叉流脱除PM2.5的影响

本文针对气液交叉流中液柱阵列脱除气相PM2.5过程的颗粒湍流扩散和热泳作用协同作用进行了实验研究和数值模拟。数学模型中引入颗粒随机轨道模型考察了热泳作用下PM2.5颗粒的运动情况,模拟结果与化学分析法和重量法的颗粒脱除实验结果进行了对比。结果表明采用重量法分析得到颗粒脱除率与化学分析法基本相同,验证了两种颗粒浓度实验检测方法的一致性;气相流速为1 m•s-1时,考虑颗粒湍流扩散影响相比于未考虑时,模拟数据与实验结果的相对偏差从-60%降至±30%,表明颗粒湍流扩散是本系统中影响颗粒脱除的重要因素。     

Influences of friction drag on spontaneous condensation in water vapor supersonic flows

A mathematical model was developed to investigate the water vapor spontaneous condensation under supersonic flow conditions. A numerical simulation was performed for the water vapor condensable supersonic flows through Laval nozzles under different flow friction conditions. The comparison between numerical and experimental results shows that the model is accurate enough to investigate the supersonic spontaneous condensation flow of water vapor inside Laval nozzles. The influences of flow friction drag on supersonic spontaneous condensation flow of water vapor inside Laval nozzles were investigated. It was found that the flow friction has a direct effect on the spontaneous condensation process and therefore it is important for an accurate friction prediction in designing this kind of Laval nozzles. Supported by the National Natural Science Foundation of China (Grant No. 50676002), the Specialized Research Fund for the Doctoral Program of Higher Education (Grant No. 20040005008) and the Beijing Best Innovation Person Selecting Project (2006)