Turbulent Flowfield Analysis in a Bluff-Body Burner Using PIV

The structure of inert turbulent flows, stabilized in a Bluff-Body burner, is studied considering different volumetric flows for Nitrogen jet and annular air in coflow configuration. Flowfield analysis on Bluff-Body burner is essential to improve the knowledge about this burner, which plays an important role in industrial applications. Thus, vector velocity field is performed, employing Particle Image Velocimetry technique. Also, an uncertainty analysis is performed considering parameters involved in this technique yielding 6% to velocity measurements. The acquired information produces the results based in flowfield structure, which are presented in terms of statistical momentum and Reynolds stress, in which Boussinesq Hypothesis is considered to incompressible flows. However, this hypothesis fails in certain conditions. In this way, is possible to comprehend and provide experimental data from the turbulent effects on the flowfield and also contribute to predict the combustion flows, in order to enable the validation and develop numerical models.

Flowfield characteristics in sidewall compression inlets

In this work,the flow fields in three-dimensional(3D)sidewall compression inlets are investigated theoretically and numerically.Combining spatial dimension reduction theory with the shock dynamics theory,a detailed analysis of the flowfield in the compression part of an inlet is proposed.Using this analytical approach,wave configurations are determined and flowfield parameters are solved;numerical simulations are conducted to validate these theoretical results.The effects of the attack angle and yaw angle on the pressure ratio,wave structures,and total pressure recovery performance are discussed in detail.Findings offer an effective way to study shock/shock interaction(SSI)in sidewall inlets,which is essential to the designing of such inlets.

Effects of Nozzle-Strut Integrated Design Concepton on the Subsonic Turbine Stage Flowfield

In order to shorten aero-engine axial length,substituting the traditional long chord thick strut design accompanied with the traditional low pressure(LP) stage nozzle,LP turbine is integrated with intermediate turbine duct(ITD).In the current paper,five vanes of the first stage LP turbine nozzle is replaced with loaded struts for supporting the engine shaft,and providing oil pipes circumferentially which fulfilled the areo-engine structure requirement.However,their bulky geometric size represents a more effective obstacle to flow from high pressure(HP) turbine rotor.These five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD,and hence cause higher loss.Numerical investigation has been undertaken to observe the influence of the Nozzle-Strut integrated design concept on the flowfield within the ITD and the nearby nozzle blades.According to the computational results,three main conclusions are finally obtained.Firstly,a noticeable low speed area is formed near the strut's leading edge,which is no doubt caused by the potential flow effects.Secondly,more severe radial migration of boundary layer flow adjacent to the strut's pressure side have been found near the nozzle's trailing edge.Such boundary layer migration is obvious,especially close to the shroud domain.Meanwhile,radial pressure gradient aggravates this phenomenon.Thirdly,velocity distribution along the strut's pressure side on nozzle's suction surface differs,which means loading variation of the nozzle.And it will no doubt cause nonuniform flowfield faced by the downstream rotor blade.

Analysis of Cold Flowfield of Multi-Annular Opposed Jets

The technique of the use of multi-annular opposed jets as different from using swirl and bluff body creates an excellent recirculation zone with desired size in a large space.The size of recirculation,the magnitude of reverse velocity and turbulence intensity are much greater than those formed by bluff body.Factors affecting the flowfield include the velocity ratio of the opposed jets to the primary air J,the diameter and construction of the opposed jet ring,secondary air velocity and configuration,and confined or unconfined flow condition and so on.This method is a promising way for flame stabilization in combustion technology.

Sivells方法在高马赫数低总压喷管设计中的适用性分析

目前高超声速轴对称型面喷管广泛采用Sivells方法进行无黏型面设计,通过求解轴对称的von Kármán动量方程进行边界层修正。该方法在常规高超声速风洞、激波风洞等的高马赫数、高总压条件下已成功应用,但鲜有在高马赫数、低总压条件下的应用研究。在低总压条件下,采用该方法设计了马赫数6、8、10、12的轴对称型面喷管,通过数值模拟分析流场结构,并进行试验验证;模拟了喷管射流流场,通过对射流流场进行结构分析,判断设计方法的适用性。研究结果表明:马赫数6、8喷管流场与设计基本一致,射流流场品质较好,适合开展风洞试验;马赫数10、12喷管流场局部过度膨胀,马赫数高于设计值,其中马赫数10喷管的射流流场品质较好,马赫数12喷管的射流流场品质下降显著且马赫数轴向梯度增大。因此,在高马赫数、低总压条件下,Sivells设计方法仍适用于马赫数6、8喷管,马赫数10喷管处于临界状态,而不适用于马赫数12喷管。

Design Optimization of Outlet Temperature Distribution of Hydrogen Micromixing Diffusion Combustor Based on Micro-turbojet Engine Engine

This paper focuses on the optimization of the outlet temperature field of a hydrogen micromixing diffusion combustor for a micro-turbojet engine with a thrust of 20kgf.The joint simulation optimization platform was established combiningWorkbench and UG and the multi-parameter driven optimization design process was developed.The surrogate models and genetic algorithms were employed to investigate the influences of key parameters on the hotspot temperature at the combustor exit.It was found that smaller diameters of the dilution holes and positions further from the exit lead to lower hotspot temperatures.Additionally,an optimal solution for achieving a uniform temperature distribution at the combustor outlet was obtained.This solution involves a single row of dilution holes on both the inner and outer walls of the flame tube,arranged in an alternating axial and angular pattern.Through aerothermal process analysis,it was determined that the outlet temperature distribution coefficient(OTDF)of the combustion chamber is below 0.2.Meanwhile,the axial dimension of the flame is short,approximately one-third of the flame tube length.The conclusions derived from this study provide important guidance for the design of hydrogen micromix diffusion combustor.

旋转爆震火箭发动机推进性能分析

针对旋转爆震发动机(Rotating Detonation Engine,RDE)燃烧室简化二维流场,采用流场分区,建立了一种适用于RDE工作特性的性能分析模型,可快速准确地估算RDE的推进性能。模型考虑了燃烧室内气流膨胀过程中的气流角度匹配,可准确描述存在单个爆震波时的基本流场结构特征,包括爆震波倾斜角度、斜激波角度、滑移线角度等,结果与已有文献的研究结果一致性较高。根据模型流场中所取控制体的进出口参数,可得理想膨胀状态下RDE的推进性能,估算结果与已有性能估算模型吻合较好,与已有实验数值偏差为8%。经验证推导,模型亦可用于多波模态。采用该性能分析模型对比研究了不同反应物当量比、进气总压和总温下火箭式RDE的推进性能。研究表明,性能分析模型可准确反映RDE燃烧室的非稳态流场特征,且可快速准确地估算RDE的推进性能,为RDE推进性能的评估提供了简便可靠的方法。

0.75m×0.50m结冰风洞气动——热流场品质评估

结冰风洞气动—热流场品质是结冰风洞开展试验应用的先决条件,为评估0.75m×0.50m结冰风洞的气流场和热流场品质,依照SAE ARP 5905结冰风洞标准,对0.75m×0.50m结冰风洞的气流场和热流场开展符合性校测试验,考察试验段中心截面的气流速度场、方向场和温度场品质,获得试验段气流速度修正关系和气流总温修正关系。结果表明:试验段气流速度空间最大偏差小于±2%,且试验段气流速度空间均匀性会随着气流速度的增大而得到改善;试验段气流偏角空间最大偏差小于0.8°;气流总温在-20℃以内时,空间均匀性可达到±1℃,气流总温为-30℃时,空间均匀性可达±2℃;0.75m×0.50m结冰风洞的气动—热流场品质符合SAE ARP 5905要求。

涡旋压缩机吸气过程流场特性研究

针对涡旋压缩机吸气过程产生的预压缩现象,为了探明其产生机理和对压缩过程的影响以及流场的变化规律,基于计算流体动力学原理,在不同曲轴转速条件下,运用三维动网格技术对涡旋压缩机内部流场进行数值模拟计算。结果表明:吸气腔与两侧进气流道的流场分布均不对称,不同曲轴转角时进气流道、吸气腔等位置产生强度不同的涡流区;随着曲轴转速的提升,吸气过程预压缩现象发生时曲轴转角提前约10~21°不等,引起吸气腔内压力升高23.5%~29.0%,使得实际吸气量与理想吸气量不再相等,涡旋齿尾部涡流现象随之加剧。

探针支杆改变对测点处结果及流场影响研究

以小尺寸高负荷增压级中介机匣流道为对象,采用数值模拟的方法研究了无探针、探针支杆直径为12 mm及12×6 mm腰型支杆测点处总温总压及支杆尾迹对流场影响。结果表明:腰型支杆进出口总压损失较圆柱支杆较小;改变探针支杆对测点处总温及总压脉动结果影响较大;支杆尾迹对流场周向影响可达数倍支杆尺寸。

低比转速离心泵内部流场分析及试验

为了研究低比转速离心泵内部流动特性,对10种不同设计方案的低比转速离心泵进行了数值模拟和性能预测,讨论了叶轮和蜗壳的关键几何参数对内部流场和外特性的影响,分析了不同设计方案下泵内的静压、流线、速度和湍动能等分布,并针对复合式叶轮短叶片的分布位置和蜗壳喉部面积进行了对比试验。试验结果表明,该文优选的方案D,通过增加偏置短叶片后,扬程提高了5.5m,效率提高了3.23%;增大蜗壳内部和喉部面积后,5种设计方案的额定点扬程均提高了约10m,效率提高了约5%,且扩大了高效区范围。该研究将为低比转速离心泵的性能优化提供一定的科学依据。

改善内乘波式进气道出口均匀性的内收缩基本流场研究

内收缩基本流场的设计直接决定了内乘波式进气道最终性能。以出口流场均匀为目标,提出了两种新型内收缩流场,分别命名为ICFC流场和ICFD流场并给出了相应的设计方法。以来流马赫数6.0和出口马赫数3.0为条件,设计了含截短Busem ann流场在内的几种典型三维内收缩流场,开展了流场分析和性能对比。综合分析后发现,在保证流场具备较高性能参数的前提下,ICFC流场出口参数最均匀,更适合于内乘波式进气道设计。初步研究获得的ICFC流场主要性能参数随入口气流偏转角的变化规律,为改善内乘波式进气道出口均匀性设计提供了依据。

W火焰锅炉结渣特性数值模拟

采用结渣模型耦合气固两相流动燃烧模型,对一台DG1025/18.2–II14型W火焰锅炉结渣特性进行了数值模拟,结合现场运行状况,对结渣位置、程度及原因进行了分析。结果表明,该锅炉的结渣位置主要是下炉膛侧墙、拱部燃烧器区域和前后墙局部区域。炉膛中心区域温度比两侧高,气流膨胀更迅速,压力更高,挤压两侧气流沿炉膛宽度方向向侧墙运动,产生偏斜,火焰冲刷侧墙,是导致W火焰锅炉侧墙结渣的根本原因。锅炉变工况运行时,切停或切换部分燃烧器,使炉内局部空气动力场偏斜,冲刷已关闭了燃烧器的拱部和前后墙区域,则是导致拱部燃烧器区域和前后墙局部区域结渣的主要原因。

水滴撞击特性的数值计算方法研究

对水滴撞击特性的数值计算方法进行了研究。在对防冰部件流场进行计算的基础上 ,通过对水滴所在单元的判断和单元内流场速度的插值求解以及水滴运动轨迹计算边界的判断 ,采用差分法对水滴运动方程进行了数值求解 ,得到了水滴运动轨迹 ,从而确定了水滴的撞击极限、总收集系数和局部水收集系数等水滴撞击特性参数 ,为飞机防冰系统的设计奠定了基础 ;此外 ,以发动机进气道的水滴撞击特性的计算为算例 ,研究了飞行高度、飞行速度及水滴半径对水滴撞击特性的影响。

等离子体气动激励抑制高负荷压气机叶栅流动分离的实验研究

为揭示等离子体气动激励抑制高负荷压气机叶栅流动分离的作用效果和主要影响因素,在不同流场和激励条件下开展了等离子体流动控制的实验研究,介绍介质阻挡放电等离子体的产生原理与放电图像,利用栅后压力分布分析研究叶栅内部流场结构以及等离子体激励的变化规律和主要影响因素。结果表明:等离子体气动激励抑制附面层流动分离的作用效果随气流速度的增大逐渐下降,在攻角为2°时最佳,然后随攻角的增大激励效果显著下降;激励器电极的放电位置至关重要,在靠近角区分离线的起点时的激励效果明显强于其他位置;对等离子体气动激励的作用方式进行优化,变定常激励为非定常激励,使其与分离区的时间尺度实现最佳的耦合,是提高等离子体流动控制效果的一个重要途径。

产出液预分离水力旋流器的机理及试验研究

根据油田生产需要，从试验分析出发，提出了水力旋流器的部分结构参数与操作参数之间的几个重要的关系式，进而研制开发了用于高含水油井产出液预分离的水力旋流器。并通过对其流场特性的分析发现，预分离水力旋流器的溢流口直径加大后，为提高预分离效率，必须将溢流管伸入旋流腔一定长度，同时操作参数也应控制合理。以此为依据试制出样机。油田现场试验证明，含水量在８５％左右的油井产出液经预分离水力旋流器处理后，其溢流含水量完全可达到小于３０％的指标，而底流水中含油也可降至１％左右，基本满足了处理后的水质指标要求，可在油田上推广应用。

轴向间隙引气对双级轴流式压气机性能及流场影响的数值研究

采用数值模拟的方法,研究了引气对某双级轴流压气机气动性能的影响。数值计算所获得实壁机匣总性能与试验结果符合良好,结果表明,在靠近第二级转子前缘处的机匣引气能够有效地提高压气机的失速裕度的同时,对压气机的压比和效率影响较小,分析了引气对压气机顶部区域流场结构的影响。

气动塞式喷管的流场数值模拟和设计参数探讨

针对气动塞式喷管流场中存在的激波、激波与附面层相互作用、大尺度分离流动等复杂的物理现象 ,本文采用扩展的压强校正法求解用紊流模型封闭的可压缩湍流平均 N-S方程组 ,利用交错网格系统抹平迭代过程中的数值振荡 ,并通过高分辨率的 TVD格式进一步改善压强校正法的激波捕获效果 ,对气动塞式喷管的流场进行了详细的数值模拟。并进一步探讨了喷管倾角、塞锥长度和二次流流量比对喷管流场结构和性能的影响。

空心弹丸流场数值模拟与阻力特性

采用隐式有限体积TVD(总变差减小)数值格式,在超声速条件下数值模拟了某空心弹丸绕流流场,系统研究了流场波系结构与空气阻力特性,证实空心弹丸阻力系数比普通弹丸小得多,同时发现发射角度对于空心弹丸的速度降影响不大。

水平轴风力机尾迹流场PIV实验研究

在水平轴风力机模型不同尖速比条件下,利用PIV粒子图像测速技术对风轮尾迹流场进行了测量。采用锁相平均测量技术,获得了风轮尾迹流场的瞬时速度场、时均速度场、涡量场等有关定量信息,为准确计算风力机的流场、载荷和气动特性等提供了依据。实验结果表明:风轮叶片尾缘后侧的尾迹中存在轴向速度亏损区。尾迹在叶片尾缘生成后,随即发生膨胀。直到风轮下游2倍弦长以后,尾迹低速区逐渐衰减,轴向速度不断增加,尾迹区同时发生收缩现象。风轮尾迹涡从叶片尾缘脱落后,在向下游发展传播过程中,尾迹涡的涡心所形成的运动轨迹是与风轮叶片旋转方向相反的螺旋线,涡量数值随着螺旋线向风轮下游的延伸而减小。由于风力机叶片数少,相邻叶片之间的尾迹基本上不存在互相干扰的现象。