固液两相流下离心泵内特性和颗粒分布的数值模拟研究北大核心CSCD

基于计算流体动力学(CFD)和数值模拟的方法,研究固液两相流下的离心泵内特性变化规律、颗粒分布和速度,从而进一步探索离心泵的磨损规律。计算结果表明,颗粒的浓度和密度对离心泵内特性存在一定的影响,总压和湍动能系数k(液相)随着θ角度增大呈现出周期性波动的现象,并且总压和湍动能系数k(液相)在不同的工作条件下的波动的规律比较相似。在不同的颗粒浓度下,蜗壳中固相颗粒浓度沿着蜗壳半径方向向外逐渐增大,其中隔舌出口附近的蜗壳内边缘处的浓度最高,且在隔舌出口附近颗粒分布较为不均匀。此外,颗粒密度对颗粒在离心泵内分布的影响较为明显。相比于大密度颗粒工况,当颗粒密度较小时,离心泵流道内颗粒分布较为均匀。颗粒速度大小和浓度的分布在叶片的工作面和背面有着明显的不同,在叶片工作面上,颗粒在叶轮进口附近易集中,在叶片背面上,颗粒在叶轮进口附近和叶片末端易集中,从而推断在叶片工作面入口上边缘处和在叶片背面的末端磨损更有可能被磨损。     

固液两相流下离心泵内特性和颗粒分布的数值模拟研究

基于计算流体动力学(CFD)和数值模拟的方法,研究固液两相流下的离心泵内特性变化规律、颗粒分布和速度,从而进一步探索离心泵的磨损规律。计算结果表明,颗粒的浓度和密度对离心泵内特性存在一定的影响,总压和湍动能系数k(液相)随着θ角度增大呈现出周期性波动的现象,并且总压和湍动能系数k(液相)在不同的工作条件下的波动的规律比较相似。在不同的颗粒浓度下,蜗壳中固相颗粒浓度沿着蜗壳半径方向向外逐渐增大,其中隔舌出口附近的蜗壳内边缘处的浓度最高,且在隔舌出口附近颗粒分布较为不均匀。此外,颗粒密度对颗粒在离心泵内分布的影响较为明显。相比于大密度颗粒工况,当颗粒密度较小时,离心泵流道内颗粒分布较为均匀。颗粒速度大小和浓度的分布在叶片的工作面和背面有着明显的不同,在叶片工作面上,颗粒在叶轮进口附近易集中,在叶片背面上,颗粒在叶轮进口附近和叶片末端易集中,从而推断在叶片工作面入口上边缘处和在叶片背面的末端磨损更有可能被磨损。     

涡轮增压器压气机叶片振动分析

本文针对某种型号涡轮增压器存在进气口振动、噪声大等问题，先通过三维坐标仪对该涡轮增压器叶轮叶片曲面轮廓进行坐标测量，然后用CAD软件进行三维建模，并利用有限元软件对叶轮大小叶片进行了模态分析，得出了叶片的各阶固有频率以及相应振型。对比增压器压气机的工作转速和叶轮片通过频率，找出叶片共振的频率，从而为有效地控制压气机进气口振动、噪声大等问题提供理论依据。     

民用航空器APU压气机第一级叶轮损伤分析

以航空器APU压气机第一级叶轮损伤为研究对象,详细分析了APU压气机第一级叶轮断口的形貌、化学成分、金相组织.研究结果表明,APU第一级叶轮叶片掉块和裂纹均属于疲劳断裂,疲劳导致叶片掉块和开裂.叶片疲劳可能与叶盆根部表面存在显微缺陷有关,显微缺陷可能是由于叶轮工作中微小颗粒随气流在叶盆表面冲蚀的结果,它们的存在加重了局部应力的集中,形成了疲劳的起源.叶片前缘损伤部位通过能谱分析未发现外来元素,但不排除外来物击伤叶片前缘的可能性.该分析结果将有助于飞行事故的调查并得出正确的失效分析结论.     

离心式压缩机叶轮裂纹成因分析及预防

针对某冷水机组离心式压缩机一级叶轮进风口叶片出现裂纹问题,采用扫描电镜与能谱分析,发现在断裂源区存在沿晶裂纹、鸡爪纹、氯与硫离子,在叶片根部形成枝状裂纹。利用ANSYS软件对叶轮建模及模拟,结果表明,进风口第一主应力在叶轮叶片根部达到最大,为363.61 MPa,小于材料的抗拉强度,裂纹走向与第一主应力垂直,确认为工作环境导致的应力腐蚀裂纹,最后提出降低叶轮焊接应力及优化结构可靠性方案。     

快速加热过程中Fe-40Ni-Ti合金的晶粒长大行为

利用热模拟技术、金相观察及定量统计,通过分析Fe-40Ni-Ti合金快速升温过程中试样不同部位的晶粒长大规律,模拟研究了焊接过程中奥氏体晶粒的长大行为.结果表明:温度最高的中心线附近晶粒长大显著,5 s内温度达到1350℃时,其尺寸达到了180 μm;而距离中心线4 mm处的热影响区及母材(试样端部)晶粒变化不大,在80 μm左右.金相观察发现TiN颗粒对晶界迁移产生了明显的阻碍作用.     

某发动机压气机四级转子

对某发动机经８０ｈ试车后四级压气机３５＃转子叶片榫头折断故障做了分析，经金相与扫描电镜观察和模拟试验，使故障再现，分析认为，是加工配合过盈，局部接触应力过大出现微振磨损所致，并提出改进措施。     

钛合金叶片燃烧后冷却过程的三维热流耦合数值模拟

为了理解航空发动机钛火发生后叶片的冷却过程,采用有限元方法结合ROTOR37转子模型,分别对550℃阻燃钛合金(TF550钛合金)和600℃高温钛合金(TA29钛合金)燃烧后压气机通道内温度场、流场进行数值模拟研究。结果表明:相对马赫数对于压气机通道内叶片散热有一定的影响,其中叶尖燃烧区域在0.7~1的低马赫数区域散热能力最佳;相对于前缘燃烧区域,叶尖燃烧区域的冷却过程更为复杂,且冷却速率比前缘燃烧区域低一个数量级;在叶尖燃烧区域内,TF550钛合金和TA29钛合金的冷却温度差异比较显著,在1000~2500K温度区间内的差别最大,前者比后者低100K以上,在300~500K温度区间内前者比后者低30K以内;叶尖燃烧区域流场的温度畸变会增加喘振的剧烈程度,设计叶片时应充分考虑燃烧对喘振裕度的影响。     

离心泵瞬态空化流动及压力脉动特性

基于RNG k-ε湍流模型及输运方程空化模型,考虑空化流动可压缩性影响修正湍流模型,考虑湍流压力脉动对饱和压力影响修正空化模型,对小流量工况离心泵瞬态空化流动进行数值模拟,计算所得扬程随进口压力变化曲线与试验结果吻合较好,能较准确预测离心泵在空化临界点扬程陡降过程。在离心泵叶轮流道中间与叶片压力面、吸力面布置监测点,对比分析非空化、空化时叶轮内压力脉动特性。结果表明：叶轮内压力脉动主频为叶轮转频;在叶轮流道及叶片吸力面,叶轮内压力脉动最大幅值由进口至出口逐渐增大,而在叶片压力面,压力脉动最大幅值在叶片进口4/5处最大。空化流动各监测点压力脉动最大幅值大于非空化,在流道进口处约为非空化时2倍。受蜗舌结构影响,叶轮内各流道空化区域分布不均匀。     

颗粒形状对弯管冲蚀磨损影响的数值模拟研究

为了研究输气管内不同形状固体颗粒对弯管冲蚀磨损特性的影响,预测弯管内壁受到冲击后磨损分布情况,采用计算流体动力学(CFD)来计算气体流动,采用离散单元法(DEM)来计算颗粒运动,其中非球形颗粒采用超椭球模型进行建模,并用切向撞击能量磨损模型(SIEM)来计算弯管磨损。模拟结果表明,在相同气速条件下,尽管不同形状颗粒在管中的运动状态差别不明显,但是对应的管道内壁磨损情况却有很大差异:颗粒越接近方形,造成的弯管最大磨损率越高,磨损严重范围也随之增大,但最大磨损率的位置会趋于稳定;弯管内长椭球颗粒发生滑动摩擦概率更高,扁椭球颗粒发生滚动摩擦的概率更高,这导致了长椭球颗粒对弯管总磨损率高于扁椭球。比较不同气速下颗粒形状对弯管磨损程度的影响,发现升高气速仅会均匀增大弯管磨损,最大冲蚀位置并不会改变。     

涡轮增压器压气叶轮爆裂转速数值分析与试验研究

随着内燃机不断向高效率、大功率、智能化方向发展,其核心部件涡轮增压器逐渐向高压比、高转速、大流量方向迈进。由于涡轮增压器压气叶轮的转速非常高,压气叶轮爆裂尤其是产生非包容性碎片时会对内燃机运行安全造成严重危害,甚至造成人员伤亡,因此研究涡轮增压器的包容性尤为重要。基于有限元法,针对涡轮增压器包容性(压气叶轮的爆裂转速和弱化方式),分别运用线弹性材料模型及双线性等向强化弹塑性材料模型模拟了涡轮增压器压气叶轮在离心载荷作用下的爆裂转速,并对完整压气叶轮及2种弱化处理的压气叶轮进行了包容性试验。结果表明:运用双线性等向强化弹塑性材料模型计算得到的压气叶轮爆裂转速与试验值约相差2%,而运用常规线弹性材料模型计算得到的压气叶轮爆裂转速与试验值约相差16%,偏保守。同时,2种弱化处理的压气叶轮均在预定转速下爆裂,验证了弱化方式的合理性与准确性;通过控制开槽的尺寸即可实现压气叶轮在预定转速下爆裂。研究结果为后续涡轮增压器压气叶轮包容性分析奠定了基础。     

Isotropie der turbulenten Wirbelströmung in Seitenkanalverdichtern

The impeller with a high number of blades causes a turbulent vorticity flow in the side channel, which is the reason for the specific impuls flow and the energy transfer in the side channel. High frequency pressure oscillations were caused according to the changes of the vorticity structure in the side channel. The dissipation loses are the reason for the heat up of the gas during the compression. According to the transported gas mass flow the turbulent vorticity flow is superposed from the average flow velocity of the gas. They depend from the peripheral speed of the impeller and the size of the compressor. The superposition of the turbulent vorticity flow and the average flow velocity cause the question of the isotrope of the turbulent vorticity flow in the side channel for the working area of the compressor. Experimental results from side channel compressors will give an answer to this.     

Dämpfung von Rotating Stall in Radialverdichterstufen

In part load span centrifugal compressors incline rotating stall in the impeller, which often causes transient pressure oscillations and surge. Operation in part load span with transient processes has to be avoided, because it can endanger the compressor and the plant by vibrations. Active devices like an upstream or downstream side channel stage can influence flow and unsteady gas pressure oscillations in centrifugal compressor stages and shift rotating stall to lower flow or entirely avoid it. This article shows experimental results for characteristic lines and unsteady gas pressure oscillations in centrifugal compressor stages, which where coupled with an downstream side channel stage. The enforced turbulent eddy flow with unsteady gas pressure oscillation in side channel stages diminishes unsteady gas pressure oscillation in the centrifugal compressor stage and limits pressure gradient as well as the maximum reachable value of gas pressure oscillation at rotating stall.     

Modified zirconia abradable seal coating for high temperature gas turbine applications

The results and development of a new full ceramic abradable turbine seal coating material prepared by thermal spraying are presented. The main objective was to achieve high temperature abradability and low mating part wear using an erosion-resistant coating with high temperature stability and thermal shock resistance. The new coating was successfully laboratory tested at temperatures of at least 1100°C (2012°F). Commercial metal-based abradable coatings which are currently available are limited to lower operating temperatures. Typical plasma- sprayed ceramic coatings, because of inherent high particle velocities, are normally to dense to permit abrading without experiencing high turbine blade tip wear damage. In contrast, lower velocity combustion-sprayed ceramic coatings frequently have lower toughness and cohesive particle strength for resistance to abrasive erosion. The new coating material is designed to react exothermically, during combustion spraying, to produce a coating both with high interparticle cohesive strength for resistance to abrasive particle erosion and with controlled porosity for low turbine blade tip wear and effective abradability. Adjustment of spraying conditions gives flexibility to alter the coating hardness and porosity and permits the tailoring of abradability and erosion resistance properties for specific operating requirements.Based on specially developed test methods for high temperature abradability, high temperature particle erosion and thermal cycling, the modified zirconia coating showed superior performance to high performance baseline materials tested in the program. Industrial evaluation of this coating is presently being conducted.     

Deposition of a nanocomposite (Ti,Al, Si)N coating with high thickness by high-speed physical vapor deposition

Nanocomposite coatings such as (Ti, Al, Si)N have been demonstrated as promising candidates for the use as protection against solid particle erosion for compressor blades. Typically, nanocomposite (Ti, Al, Si)N coatings are deposited by different physical vapor deposition (PVD) techniques. However, the relatively low coating thickness up to a few micrometers due to low deposition rates leads to a limited lifetime of the coatings under erosive particle bombardment. In this study, the deposition of a nanocomposite (Ti, Al, Si)N coating was performed by a hollow cathode gas flow sputtering method, the high-speed physical vapor deposition, which enables the high-rate deposition of thick coatings. Morphology and microstructure of the coating were investigated via scanning electron microscopy and transmission electron microscopy, respectively. Tribological characterization by impact tests and erosion tests demonstrates that the nanocomposite (Ti, Al, Si)N coated sample reveals a promising resistance against impact loads and the solid particle erosion. Summarily, nanocomposite (Ti, Al, Si)N coatings deposited by the high-speed physical vapor deposition provide a high potential for the erosion protection of compressor blades.     

Erosion in the tube entrance region of an air-cooled heat exchanger

Erosion in the tube entrance region of a typical air-cooled heat exchanger is numerically predicted. The erosion rates are obtained for different flow rates and particle sizes assuming low particle concentration. The erosion prediction is based on using a mathematical model for simulating the fluid velocity field and another model for simulating the motion of solid particles. The fluid velocity model is based on the solution of the time-averaged governing equations of 3-D turbulent flow while the particle-tracking model is based on the solution of the governing equation of each particle motion taking into consideration the viscous and gravity forces as well as the effect of particle rebound behavior. The computational model was validated against available experimental data and the comparison resulted in a good agreement. The investigation covered particle sizes from 10 to 350 μm and inlet flow velocities from 0.18 to 4.5 m/s. The results show that the location and number of eroded tubes depend mainly on the particle size and flow velocity at the header inlet. The total rate of erosion was found to increase exponentially with flow velocity. At high flow velocities, the maximum total erosion rate results from large particles and the effect is reversed at low velocities. Similarly, the tube penetration rate was found to increase with the increase of flow velocity for all particle sizes. At the typical velocity of 1.1 m/s, the minimum tube lifetime was caused by the 350 μm particles and the maximum was caused by the 200 μm particles. Based on the obtained results, it is well established that erosion cannot be totally avoided so long as solid particles are present in the fluid. However, the threshold velocity below which erosion is negligible can be accurately defined if an acceptable lifetime (or penetration rate) is defined.     

多级冲压泵固液两相流冲蚀特性

基于离散相模型和标准k-ε湍流模型,对多级冲压泵首级和次级流场进行数值模拟。计算不同固相颗粒质量浓度时的外特性和过流部件冲蚀特性,分析颗粒体积分数分布、流场速度和颗粒运动轨迹,研究其对冲蚀特性的影响。结果表明:随着颗粒浓度的上升,冲压泵的单级扬程和效率线性衰减,当颗粒质量浓度为90 kg/m^3时,单级扬程下降6.89%,效率下降6.95%;叶轮和导叶的冲蚀率与颗粒质量浓度指数正相关,叶片与后盖板的连接处、导叶叶片转弯部分的磨损率最高;较高的颗粒浓度与冲击速度、更为频繁的颗粒冲击是造成上述区域较高的冲蚀率的主要原因。     

Particle scale study on heat transfer of gas–solid spout fluidized bed with hot gas injection

ABSTRACT

In this paper, the heat transfer characteristics of a 2D gas–solid spout fluidized bed with a hot gas jet are investigated using computational fluid dynamics-discrete element method. The initial temperature of the background gas and particles in the spouted bed was set to 300?K. The particle temperature distribution after injection of 500?K gas from the bottom, center of the bed, is presented. The simulation results indicate well heat transfer behavior in the bed. Then, statistical analysis is conducted to investigate the influence of inlet gas velocity and particle thermal conductivity on the heat transfer at particle scale in detail. The results indicate that the particle mean temperature and convective heat transfer coefficient (HTC) linearly increase with the increase in inlet gas velocity, while the conductive HTC and the uniformity of particle temperature distribution are dominated by the particle thermal conductivity. The conductive and convective heat transfer play different roles in the spout fluidized bed. These results should be useful for the further research in such flow pattern and the optimization of operating such spouted fluidized beds.     

Kombination von Radial- und Seitenkanalstufen für Turboverdichter

Unsteady gas pressure oscillations occur at impeller outlet and diffuser of radial and side channel compressors, engendered by the blades grid of the impeller. They have effect beyond the limits of inlet and outlet. If a radial stage is coupled to a side channel stage, then the unsteady gas pressure oscillations of the side channel stage have an effect inside the radial stage affecting flow and characteristic curve. Because of that, the radial stages unstable characteristics and the limit of rotating stall can be moved to lower volume flows or completely suppressed by connecting a side channel stage before or behind it. Therefore the permissible range of operation of combined compressor stages can be extended compared with a radial compressor stage. Moving the limit of rotating stall of the radial compressor stage and lower the gas pressure oscillations caused by Rotating Stall as a result of the side channel stages unsteady gas pressure oscillations will be proved experimental. As a criterion for Rotating Stall in radial compressor stages also the proportion between RMS of gas pressure oscillations and the total pressure increase in the radial compressor stage can be used.