Effects of the Blade Shape on the Trailing Vortices in Liquid Flow Generated by Disc Turbines

Particle image velocimetry technique was used to analyze the trailing vortices and elucidate their rela-tionship with turbulence properties in a stirred tank of 0.48 m diameter,agitated by four different disc turbines,in-cluding Rushton turbine,concaved blade disk turbine,half elliptical blade disk turbine,and parabolic blade disk turbine.Phase-averaged and phase-resolved flow fields near the impeller blades were measured and the structure of trailing vortices was studied in detail.The location,size and strength of vortices were determined by the simplified λ2-criterion and the results showed that the blade shape had great effect on the trailing vortex characteristics.The larger curvature resulted in longer residence time of the vortex at the impeller tip,bigger distance between the upper and lower vortices and longer vortex life,also leads to smaller and stronger vortices.In addition,the turbulent ki-netic energy and turbulent energy dissipation in the discharge flow were determined and discussed.High turbulent kinetic energy and turbulent energy dissipation regions were located between the upper and lower vortices and moved along with them.Although restricted to single phase flow,the presented results are essential for reliable de-sign and scale-up of stirred tank with disc turbines.

Aeroelastic prediction and analysis for a transonic fan rotor with the“hot”blade shape

This paper focuses on aeroelastic prediction and analysis for a transonic fan rotor with only its“hot”(running)blade shape available,which is often the case in practical engineering such as in the design stage.Based on an in-house and well-validated CFD solver and a hybrid structural finite element modeling/modal approach,three main aspects are considered with special emphasis on dealing with the“hot”blade shape.First,static aeroelastic analysis is presented for shape transformation between“cold”(manufacturing)and“hot”blades,and influence of the dynamic variation of“hot”shape on evaluated aerodynamic performance is investigated.Second,implementation of the energy method for flutter prediction is given and both a regularly used fixed“hot”shape and a variable“hot”shape are considered.Through comparison,influence of the dynamic variation of“hot”shape on evaluated aeroelastic stability is also investigated.Third,another common way to predict flutter,time-domain method,is used for the same concerned case,from which the predicted flutter characteristics are compared with those from the energy method.A well-publicized axial-flow transonic fan rotor,Rotor 67,is selected as a typical example,and the corresponding numerical results and discussions are presented in detail.

Numerical study on morphological characteristics of rotational natural supercavitation by rotational supercavitating evaporator with optimized blade shape

In view of the supercavitation effect, a novel device named the rotational supercavitating evaporator (RSCE) has been designed for the desalination. In order to improve the blade shape of the rotational cavitator in the RSCE for the performance optimization, the blade shapes of different sizes are designed by utilizing the improved calculation method for the blade shape and the validated empirical formulae based on previous two-dimensional numerical simulations, from which the optimized blade shape with the wedge angle of 45° and the design speed of 5 000 r/min is selected. The estimation method for the desalination performance parameters is developed to validate the feasibility of the utilization of the results obtained by the two-dimensional numerical simulations in the design of the three-dimensional blade shape. Three-dimensional numerical simulations are then conducted for the supercavitating flows around the rotational cavitator with the optimized blade shape at different rotational speeds to obtain the morphological characteristics of the rotational natural supercavitation. The results show that the profile of the supercavity tail is concaved toward the inside of the supercavity due to the re-entrant jet. The empirical formulae for estimating the supercavity size with consideration of the rotation are obtained by fitting the data, with the exponents different from those obtained by the previous two-dimensional numerical simulations. The influences of the rotation on the morphological characteristics are analyzed from the perspectives of the tip and hub vortices and the interaction between the supercavity tail and the blade. Further numerical simulation of the supercavitating flow around the rotational cavitator made up by the blades with exit edge of uniform thickness illustrate that the morphological characteristics are also affected by the blade shape.

低肋与V形肋复合结构在双通道中的强化换热数值研究

随着燃气轮机内涡轮入口温度的升高,燃气轮机会出现热障问题,为保证燃气轮机安全运行,复合结构能够有效提高通道的冷却性能来解决此问题。采用SST k-ω湍流模型对带有低肋与V肋复合结构双通道的流动与传热特性进行了数值模拟,将圆形肋复合结构、扇叶形肋复合结构和葫芦形肋复合结构与纯V形肋在雷诺数为10 000~60 000时的传热性能进行比较,探索出综合换热效果最佳的复合结构。发现相比于纯V形肋通道,复合结构双通道的综合传热性能均得到提升,其中葫芦形肋与V形肋组成的复合结构的综合换热效果最好。葫芦肋复合结构的Nu相比于纯V形肋提高了4.33%~6.6%,f提高了0.04%~4.48%,η最佳值达到了2.13。葫芦形肋复合结构的η比45°斜方形肋和45°斜花形肋分别增大了25.51%~32.98%和4.73%~10.51%,同时,低肋与V形肋组成的复合结构综合换热性能要优于凹坑与V形肋组成的复合结构。葫芦肋复合结构有效增强通道的换热效果且压力损失增长较小,可显著提升涡轮内部冷却通道的综合换热性能。

小型高效气动立式预混装置异形桨叶工作特性研究

为解决某交联剂在预混时溶解慢、易挥发、对操作人员危害大等问题,开发了一套采用单轴异形桨叶的可远程控制的小型高效立式气动预混装置。通过有限元方法计算了四种搅拌叶片的流场特性,分析了异形桨叶和其他三种常用桨叶的总体流型、速度流线分布。结果表明,在预混转速为45 rpm时,异形叶片可实现交联剂径向流动,使旋转中心的交联剂充分混合,有效防止中心死区的出现,展现出良好的预混性能,预混时间由人工预混的6 h缩短为2 h,乙腈溶液挥发量减少了60.8%,有效解决了交联剂挥发和挂壁析出问题,提高了交联剂的预混效率。

对旋风机新形叶片流致振动特性

为了优化对旋风机的流致振动特性,以某对旋风机叶片为研究对象,通过修改翼型的方式来提出一种性能良好且具有减振功能的新形叶片。比较了两种对旋风机流场性能,采用模态分析法进行了两种叶片的共振预测,以叶片表面非定常压力脉动作为叶片所受流体激振力,采用模态叠加法计算了两种叶片监控点强迫振动响应特性。结果表明:新形叶片具有良好的气动性能,正风性能与原始风机相差不大,反风性能优于原始风机;额定转速下,一级新形叶片相较原始叶片频率余量提高了8.9%,运行更安全;新形叶片监控点振动加速度响应最大峰值均低于原始叶片,新形叶片具有良好的减振效果;相较于一级叶片监控点,二级叶片监控点处两种叶片总振动加速度级差值最大,新形叶片减振效果更明显,且最大差值约为10.83 dB。

基于刀片式激励线圈旋转的脉冲涡流探头

脉冲涡流检测裂纹时,微裂纹在感应涡流中产生的扰动微弱,检测信号的信噪比低;另一方面,单向扫查下的常规脉冲涡流探头难以获得多向裂纹检测的最大灵敏度和判断裂纹方向。提出一种采用机电旋转脉冲涡流激励线圈的检测方法,实现了多方向微裂纹的高灵敏度检测。刀片式激励线圈具有明显的聚磁性与方向性,机电旋转激励线圈后可以获得不同转角下的接收信号,将该接收信号与基准信号进行差分,提取出微小的峰值变化量,得到角度与峰值变化量之间的图谱。试验验证与测试结果表明:基于刀片式激励线圈在空心接收线圈内旋转的脉冲涡流探头不仅具有亚毫米级裂纹深度区分的检测能力,且能有效分辨裂纹方向,误差为±5°。

3D打印陶瓷型芯研究进展

陶瓷型芯是成功制造空心叶片的关键之一,它决定着叶片的尺寸精度、合格率、制备成本。但传统制造技术存在工艺复杂、制备周期长等缺点。3D打印技术具有无需模具、快速成型、个性化定制三维零件的优势,逐渐被应用于复杂形状陶瓷型芯的制备。系统总结了粘结剂喷射、激光选区烧结、浆料直写成型、光固化成型4种主流3D打印技术在陶瓷型芯领域的研究进展,及脱脂-烧结工艺对3D打印陶瓷型芯性能的影响,最后对3D打印陶瓷型芯的未来发展进行了展望。

雷达隐身措施对Caret进气道性能影响的数值计算

针对S弯Caret进气道气动与电磁散射特性研究,采用多层快速多极子(MLFMM)数值计算方法,对比分析了转子叶片转动相位角变化对进气道雷达散射截面(RCS)的影响。采用剪切应力输运(SST) k-ω湍流模型求解N-S方程,计算黏性流场并分析进气道气动性能,对比分析了扩压段的构型和吸波导流板的安装方式对进气道气动与雷达隐身性能的影响。结果表明:转子叶片相位角的变化会导致进气道RCS在同一雷达波入射角度下出现变动,但不会改变RCS随雷达波入射角度的变化规律;采用双S弯扩压段可以有效降低进气道出口畸变和提升Caret进气道的雷达隐身性能,使其在2种工况下平均RCS均小于-2 dB,由叶片旋转导致的RCS最大差值均小于-3.5 dB,但也会导致进气道临界压力的降低;安装合适的吸波导流板可以有效提升进气道的雷达隐身性能,但会造成进气道出口畸变的增加。

叶形仿生优化对离心血泵水力性能及溶血特性的影响

离心血泵的优化对于体外膜肺氧合的临床应用具有重要意义。本研究参考座头鲸在深海中作原地转身运动时其鳍状肢的流线形,重新设计血泵的叶片。采用计算流体动力学对血泵性能进行预测和评估;通过水力试验来验证数值计算的准确性;溶血预测模型采用渐进一致数值近似方法。仿真结果表明,叶片尾缘形状对出口隔舌处的流场分布和该区域的壁面剪应力分布均有显著影响;当叶片尾缘达到一定扭转角度时,叶片结构能较好地适应泵内的流场环境,但当扭转角度不足时,流场扰动反而会增大。与原模型相比,扭转角为20°的模型在转速为2500 rpm、流量为5 L/min的工况下,扬程试验结果增加11.6%,水力效率提升3.1%,溶血指数下降40.1%。总的来说,具有一定扭转角度的仿生叶片尾缘结构可以提高半开放式离心血泵的性能。

反动式工业汽轮机超高转速大流量低压级组优化

杭汽轮引进的西门子反动式工业汽轮机低压扭叶级组在转速和热力性能方面已经无法满足现有市场的需求。针对上述问题,采用优化算法对该系列叶型进行优化,同时,引入了斜T型叶根和枞树型叶根,改进了T型末叶根骑缝螺杆锁紧结构,提高了叶片和转子的材料等级,此外,还通过分析已运行的同类型低压级组的运行数据,推算出优化后级组的最大许用质量流量。综上,优化后的级组子午面尺寸未发生改变,总总效率较优化前最高提高了2.5%,最高连续转速提高了20%,且通流能力保持不变。

水平井V形岩屑床清除工具研制与应用

井筒岩屑床堆积是制约水平井安全高效钻井的主要因素之一,研究表明环空钻井液螺旋流动能够有效提升岩屑清除效率。为此,应用CFD数值模拟与实验的方法设计了一种能够产生环空螺旋流的岩屑床清除工具并进行了现场应用,结果表明:V形叶片对岩屑运移的促进效果及对岩屑床的扰动能力均要强于螺旋形和直棱形叶片,是产生环空螺旋流的首选结构形式;V形叶片的叶片长度存在最优区间,叶片高度越大效果越好,叶片数量影响较弱;现场应用表明岩屑床清除工具在强度、硬度及叶片耐磨性均满足页岩气水平井现场作业要求,工具可随钻破坏并清除岩屑床,结合起钻过程中对岩屑床堆积重点井段进划眼作业,可将顽固性大颗粒岩屑床破坏清除,有效改善井眼清洁效果。

柠条收割机圆盘锯式刀片设计与试验

柠条圆盘锯式刀片是收割机的主要零部件之一。在收割运动过程中刀片受力不均匀,且往复循环切割动作导致其易损耗。调研柠条刀片的使用性能及材料特点,研究以特种钢作为刀片基体,在刀刃部表面利用等离子弧熔覆技术进行高合金粉末涂覆,通过优化齿形和热处理工艺参数,获得较优异的耐磨性和强度。经过摩擦磨损试验和作业主体实地收割试验可知,该柠条刀片平茬效果好,使用寿命比同类产品提高了1~2倍。

加工偏差对簸箕形气膜孔冷却效果的影响

采用数值模拟方法研究了目前簸箕形气膜孔实际生产过程中存在的2种典型加工偏差对气膜冷却效果的影响,并和传统椭圆形气膜孔及理论簸箕形气膜孔进行了对比分析。结果表明:相同孔径及冷气流量下,簸箕形气膜孔的冷却效果高于椭圆形气膜孔,加工偏差会造成簸箕形气膜孔冷却效果较大程度下降。计算结果对涡轮冷却叶片实际气膜孔加工及叶片验收有一定的指导意义。

基于特征嵌入的小样本涡轮叶片缺陷识别研究

航空发动机涡轮叶片的缺陷,影响发动机可靠性与使用寿命,基于计算机视觉与深度学习技术进行叶片缺陷的自动化检测具有重要现实意义。但是,涡轮叶片图像采集环境的高度非结构化、缺陷形式高差异性,为准确的缺陷识别带来困难。针对上述问题,提出了深度特征嵌入先验网络,其核心通过引入缺陷形状先验的特征嵌入层,准确刻画缺陷的形状特征,提高模型在小样本情况下的分类准确率。实验结果表明,所提方法在小样本叶片缺陷识别问题上取得了优越性能。

基于NX的转子T型叶根槽加工程序平台开发

目前的工艺技术下,转子T型叶根槽车削工艺较为复杂。利用NX二次开发技术,研究了T型叶根槽的模块化编程方法,开发了叶根槽加工程序平台。根据基于拓扑学的曲线编码规则,对叶根槽结构进行了曲线编码,实现了T型叶根槽结构的自动识别。按工步自动导入定制化的加工模板后,批量生成了车削刀轨。通过工步顺序对车削刀轨进行排序,最终实现了叶根槽加工程序的自动生成。该平台可以减少复杂的人工重复操作,提升数控程序编制效率。研究成果可为类似典型结构专用程序的开发提供参考。

机匣包容试验的叶片根部爆破飞断方法

在航空发动机包容试验中,为满足叶片在根部失效的要求,设计了基于爆破切割技术的叶片根部飞断试验方法。通过平板静态爆破试验确定了柔爆索的切割能力,并使用柔爆索进行了真实叶片的静态爆破试验。在MTS拉伸试验机上对爆破切割后的损伤叶片进行了静拉伸试验,确定了损伤叶片的剩余强度为50~56 kN。按照静态爆破试验获得的开槽尺寸在叶片根部开槽并敷设柔爆索,采用树脂胶固定后,在立式转子试验器上采用遥控触发的方式进行了真实叶片旋转状态下的飞断试验。结果表明:在叶片两侧加工4 mm深沟槽并敷设柔爆索爆破后,叶片被柔爆索切割,并在预定飞断转速下失效飞出。飞断截面断口显示叶片中段被柔爆索的金属射流完全切断,前后缘在离心载荷作用下拉断,爆破作用没有对叶片产生附加动能,成功实现了叶片在预定转速下的根部断裂失效。

ANALYTICAL APPROACH TO AERODYNAMIC CHARACTERISTICS OF THE HELICOPTER ROTOR WITH ANHEDRAL TIP SHAPE

A new analytical approach, based on a lifting surface model and a full span free wake analysis using the curved vortex element on the circular arc, is established for evaluating the aerodynamic characteristics of the helicopter rotor with an anhedral blade tip and is emphasized to be applicable to various blade tip configurations, such as the tapered, swept, anhedral and combined shapes. Sample calculations on the rotor aerodynamic characteristics for different anhedral tips in both hover and forward flight are performed. The results on the induced velocity, blade section lift distribution, tip vortex path and rotor performance are presented so that the effect of the anhedral tip on the rotor aerodynamic characteristics is fully analyzed.

Geometrical design of blade's surface and boundary control of Navier-Stokes equations

In this article a new principle of geometric design for blade's surface of an impeller is provided.This is an optimal control problem for the boundary geometric shape of flow and the control variable is the surface of the blade.We give a minimal functional depending on the geometry of the blade's surface and such that the flow's loss achieves minimum.The existence of the solution of the optimal control problem is proved and the Euler-Lagrange equations for the surface of the blade are derived.In addition,under a new curvilinear coordinate system,the flow domain between the two blades becomes a fixed hexahedron,and the surface as a mapping from a bounded domain in R2 into R3,is explicitly appearing in the objective functional.The Navier-Stokes equations,which include the mapping in their coefficients,can be computed by using operator splitting algorithm.Furthermore,derivatives of the solution of Navier-Stokes equations with respect to the mapping satisfy linearized Navier-Stokes equations which can be solved by using operator splitting algorithms too.Hence,a conjugate gradient method can be used to solve the optimal control problem.

冲头刃口形状对冲裁的影响研究

目的研究不同冲头刃口形状对冲裁变形过程和冲头磨损情况的影响。方法采用有限元方法和实验分析了相同工况下平冲头、台阶状冲头和屋顶状冲头对坯料冲断行为的影响,以及不同刃口形状的冲头在冲裁后的磨损情况。结果冲头结构的改变使冲裁过程发生了变化,影响了冲裁时坯料内部的应力–应变分布、峰值冲裁力、裂纹扩展速度、弹性应变能和冲头单次磨损深度。屋顶状冲头在冲裁时峰值冲裁力最低,较平冲头与台阶状冲头的峰值冲裁力分别降低了15%、10%,坯料最早起裂,也最快完成断裂,坯料的高应力区域集中在凹模刃口,且该冲头冲裁时坯料内储存的弹性应变能最多,冲头工作区的单次磨损深度最小,较平冲头与台阶状冲头的单次磨损深度分别降低了84%、80%。结论屋顶状冲头使坯料在断裂前发生了更大的拉伸变形,储存了更多的弹性应变能,坯料在拉伸状态下发生了剪切变形,冲裁力更小,高应力分布的改变降低了冲裁时坯料对冲头侧面的压力,冲断后的坯料发生弹性恢复,可防止冲头回程时坯料抱紧冲头造成的二次磨损。