不同流量系数下叶顶间隙对离心压缩机模型级性能的影响

通过CFD技术,分析了不同流量系数下叶顶间隙对离心压缩机模型级性能的影响。结果表明,对于中、小流量系数模型级,叶顶间隙越大,其效率曲线下降越大,而对于大流量系数模型级,有一定的叶顶间隙可改善叶轮内流场,反而有利于离心压缩机效率性能。无论何种流量系数模型级,存在一定的叶顶间隙则可提升能头曲线。     

叶顶间隙对离心叶轮气动性能影响研究

使用非结构化网格上的有限体积法,数值研究一半开式离心压缩机叶轮的内部流场、气动性能随叶顶间隙的变化规律。对原始叶轮相对间隙α=1．8％,数值计算所得到的气动性能参数与实验值符合非常好;对大范围叶顶相对间隙α=0．9％。7．0％内6种不同叶顶间隙下该叶轮的气动性能进行数值预测,随着叶顶间隙增大,离心叶轮气动效率、压比及转矩均降低,但变化曲线与线性函数相距甚远,呈现出典型的双平台变化关系。对所研究模型,综合考虑气动及强度振动因素,叶顶相对间隙最佳值取为2．6％,计算结果对离心压缩机设计具有一定的工程指导意义。     

驻室抽气压缩机及其与风洞性能相关性研究

为了研究驻室抽气压缩机及其与风洞性能的相关性,对E71-3离心压缩机进行了性能试验,并进行了驻室抽气性能测试。试验结果表明:(1)E71-3离心压缩机实测最高压比4.516,设计点多变效率81.8%,达到了设计要求。(2)风洞运行总压升高,压缩机多变效率降低。(3)风洞试验段Ma=0.9~1.1时,驻室抽气量对风洞模型区梯度的影响不大,但驻室抽气量超过4%后风洞马赫数均方根偏差明显增大;压缩机稳定在中等转速、适量抽气量的工况,且入口流量调节阀全开,风洞流场品质较好,运行成本最低。     

叶片载荷对半开式离心叶轮气动性能的影响

为提高半开式离心叶轮的气动性能,采用数值模拟及分析方法对三种叶片载荷分布的叶轮在不同叶顶间隙下的流动特征及性能参数影响进行了量化对比,结果表明:载荷分布形式与叶顶间隙值对叶轮气动性能有影响,当载荷前置时,叶轮性能受间隙的影响最小;叶顶间隙引起的泄漏量对叶轮性能影响不明显;叶轮流道中后段的流动性能更易受载荷、叶顶间隙值等因素的影响,导致效率下降。     

简化间隙泄漏结构对离心压缩机性能影响研究

针对流量系数为0.196的大流量系数离心压缩机模型级,采用CFD方法,研究其在简化动静间隙泄漏结构时替换壁面旋转区域大小对离心压缩机流场及性能的影响。计算结果表明:叶轮出口替换间隙壁面的旋转长度小于23.33%间隙高度时预报结果相差较小,与实验值较为吻合,超过该值计算得到的多变效率与旋转壁面长度呈线性增长趋势。这主要由于旋转壁面长度小于23.33%间隙高度时,静止壁面的粘性阻力作用强行将叶轮出口盖侧高速区减速,产生了较大损失,而超过该高度时,该高速区域的形态基本发展完整,从而使得额外旋转壁面对流体做功直接增加了轮盖侧流体的总压值,增加了轮盖侧流体气流角,提高了整级性能。设计工况下,当叶轮出口旋转壁面长度等于6.67%间隙高度时,计算得到的扩压器进口周向平均气流角与考虑间隙结构时结果基本一致,得到的多变效率比考虑间隙泄漏结构时高1.56%,总压比高1.82%。由此说明不考虑动静间隙泄漏时,合理选取叶轮出口替换间隙物面的旋转长度能够保证计算结果的可靠性。     

叶片切割对轴流风机性能影响的数值研究

叶片切割是解决实际风机裕量过大问题的一种简单而有效的手段。以OB-84型动叶可调轴流风机为研究对象,模拟叶片相对切割量为5%、10%和15%时叶顶间隙改变和不变情形下风机的性能曲线变化,探讨切割量、叶顶间隙对风机内流特征和性能的影响,得到切割前后风机运行工况点的关系式。研究表明,与原风机性能相比,叶片切割后全压和效率性能曲线均有不同幅度下移,叶顶间隙不变时在设计流量附近的性能优于叶顶间隙改变时的性能,过大流量下则相反;由于轴流风机参数裕量选择过大导致风机通常运行在设计工况点左侧,因此,轴流风机叶片的切割应保持叶顶间隙不变以保证其性能下降较小;叶顶间隙对切割前后的运行工况点关联式具有显著不同的影响,所得关系式可用于确定叶片的实际切割量,对轴流风机叶片切割改造具有重要的实际应用价值。     

轮盖密封和轮盘密封对离心压缩机级性能影响的数值研究

为了探究轮盖密封和轮盘密封对压缩机级性能的影响,文章以某台氨制冷压缩机其中四级为研究对象,数值分析了考虑密封前后离心压缩机级的性能。计算结果表明:当压缩机级的静-总压比相同时,考虑密封后,离心压缩机级在整个流量工况范围内的总压比和等熵效率都有所降低,且在小流量工况时下降更为明显;在同一级中,轮盖密封泄漏比轮盘密封泄漏严重;在同一压缩机中,随着压缩机级压差的增大,密封对级性能的影响逐渐变大。考虑密封后,密封内泄漏使得离心压缩机级的性能降低,设计点的质量流量降低了约3.5至5个百分点,等熵效率降低了约1.5至6个百分点。     

叶顶间隙对离心叶轮性能影响的数值模拟

对5个不同叶顶间隙下离心叶轮通道中的流动情况进行了数值模拟,得到了不同间隙时叶轮的效率、压比随质量流量变化的性能曲线,分析了间隙对叶轮性能的影响。     

叶轮损失模型对离心压缩机性能预测的影响

针对目前离心压缩机损失模型的差异性,在总结离心压缩机叶轮损失模型的基础上,提出在计算各截面参数时采用多变系数替换绝热指数的方法.并利用MATLAB编写程序计算压缩机在不同流量和不同转速下的压比和效率.通过和单级离心压缩机性能实验数值比较,分析叶轮损失模型对压缩机性能的影响,得出了采用简化的叶轮损失模型对压缩机效率影响较大而对压比影响较小的结论.     

离心压缩机末级最佳D_4/D_2值的数值研究

考虑到离心压缩机末级各通流元件之间的相互影响,将末级叶轮、无叶扩压器和排气蜗壳组合一起对扩压器出口直径与叶轮直径的比值D4/D2进行研究,通过对不同D4/D2条件下的整级模型进行数值模拟,研究扩压器流道长短对整级性能的影响,对离心压缩机末级流场及D4/D2值变化与离心压缩机整级性能的变化关系进行了详细的对比分析.研究结果表明,D4/D2值的变化对末级整级性能有较大的影响,并存在一个使级效率为最大值的最佳D4/D2值,D4/D2过大或过小都将使整级效率下降.     

Centrifugal compressor tip clearance and impeller flow

Compressors consume a considerable portion of the electricity used in the industrial sector. Hence, improvements in compressor efficiency lead to energy savings and reduce environmental impacts. The efficiency of an unshrouded centrifugal compressor suffers from leakage flow over the blade tips. The effect of tip leakage flow on the passage flow differs between the full and splitter blade passages. In this study, the differences in the flow fields between the full and splitter blade passages were studied numerically in detail. An industrial high-speed compressor with a design pressure ratio of 1.78 was modelled. Numerical studies were conducted with six different tip clearances and three different diffuser widths. The results show that increasing tip clearance considerably increases the reversed flow into the impeller with an unpinched diffuser. The reversed flow then partly mixes into the flow in the same blade passage it entered the impeller and the rest migrates over the blade, mixing with the tip clearance flow. Furthermore, as the reversed and clearance flow mix into the wake, the wake is weakened. As pinch reduces both the reversed flow and clearance flow, the passage wakes are stronger with pinches. However, the pinch is beneficial as the losses at the impeller outlet decrease.

     

Tip clearance effect on through-flow and performance of a centrifugal compressor

Numerical simulations have been performed to investigate tip clearance effect on through-flow and performance of a centrifugal compressor which has the same configuration of impeller with six different tip clearances. Secondary flow and loss distribution have been surveyed to understand the flow mechanism due to the tip clearance. Tip leakage flow strongly interacts with mainstream flow and considerably changes the secondary flow and the loss distribution inside the impeller passage. A method has been described to quantitatively estimate the tip clearance effect on the performance drop and the efficiency drop. The tip clearance has caused specific work reduction and additional entropy generation. The former, which is called inviscid loss, is independent of any internal loss and the latter, which is called viscous loss, is dependent on every loss in the flow passage. Two components equally affected the performance drop as the tip clearances were small, while the efficiency drop was influenced by the viscous component alone. The additional entropy generation was modeled with all the kinetic energy of the tip leakage flow. Therefore, the present paper can provide how to quantitatively estimate the tip clearance effect on the performance and efficiency.     

Numerical study on unsteadiness of tip clearance flow and performance prediction of axial compressor

Numerical calculations were performed to investigate unsteady features of tip clearance leakage flow in an axial compressor. The first stage rotor of a low speed axial compressor with a large tip clearance was examined. It was confirmed that the numerically calculated performance data were in good agreement with the experimentally measured performance data. Using frequency analysis, the flow characteristic near the casing induced by tip clearance leakage flow was found to be not associated with the rotating speed of the rotor. This characteristic is called rotating instability or self-induced unsteadiness. We found that the circumferential length scale of the rotating instability of the compressor was longer than a pitch of a blade passage; therefore, a multi-blade passage was adopted to study the flow structure more precisely. The flow characteristic was described by the frequency, the circumferential length, and the phase velocity, and was changed by operating points toward stall. The behavior of the flow was characterized by circumferentially traveling waves. Hence, the mechanism governing the development of the unsteady feature was further examined in terms of the rotating wave pattern of the pressure distribution. Furthermore, the unsteady feature of the tip clearance leakage flow affected the prediction of compressor performance by altering blockage, flow turning, and loss near the casing.     

COMPARISON OF TWO METHODS TO INCREASE TIP CLEARANCE AND ITS EFFECT ON PERFORMANCE OF TURBOCHARGER CENTRIFUGAL COMPRESSOR STAGE

Tip clearance between the blade tip and casing of a centrifugal compressor can be varied through two methods:by changing the blade height(M1)or by changing the casing diameter(M2). Numerical simulations are carried out to compare these two methods and their effect on the stage and impeller performance.The impeller and diffuser are connected through rotor stator boundary using frozen rotor approach.Overall stage performance and the flow configuration have been investigated for nine tip clearance levels from no gap to 1 mm.Impeller and diffuser performances are also pre- sented separately.It has been found that the overall and impeller performance are comparatively better for M1 below tip clearance of 0.5 mm whereas M2 is found advantageous above 0.5 mm of tip clear- ance.Both M1 and M2 show performance degradation with the increase in tip clearance.Two models have been proposed for the stage total pressure ratio and efficiency,which are found to be in agree- ment with experimental results.The impeller efficiency and the pressure ratio are found to be maxi- mum at tip clearance of 0.1 mm for both the cases however minimum diffuser effectiveness is also observed at the same clearance level.Diffuser effectiveness is found to be maximum at zero gap for both cases.As it is practically impossible to have zero gap for unshrouded impellers so it is concluded that the optimum thickness is 0.5 mm onwards for M1 and 0.5 mm for M2 in terms of diffuser effec- tiveness.Mass averaged flow parameters,entropy,blade loading diagram and relative pressure fields are presented,showing the loss production within the impeller passage with tip clearance.     

自循环机匣处理对离心压气机气动性能影响分析

对比分析了带实壁机匣与带处理机匣的压气机模型在多工况下的气动性能,结果表明,在不同转速下,处理机匣结构都具有不同程度的扩稳作用,但同时也造成绝热效率有所降低,而且峰值效率损失随着转速增大而加剧;处理机匣前后槽口与叶顶通道形成的回流运动可有效地削弱激波与间隙泄漏流的强度以及二者的相互作用,有利于改善叶轮通道的气体流通性。     

两个典型离心式压缩机级静子元件中流动的数值模拟

使用NUMACA软件对两个不同流量系数的离心式压缩机级静子元件中的流动进行了数值模拟。分析了两个级无叶扩压器中的流场及其中一个级弯道和回流器中的流场。对离心式压缩机级设计提供了改进信息。     

小迷宫密封间隙对离心制冷压缩机性能的影响

为探讨小迷宫密封间隙设计条件下离心制冷压缩机性能变化规律,以离心制冷压缩机为研究对象,通过CFD方法对压缩机叶轮和迷宫密封内的流动进行模拟.研究结果表明:迷宫密封内的流体压力近似呈阶梯状降低;在叶轮入口流量相同时,随密封间隙增大,泄漏量和泄漏损失系数在小流量工况下增大的幅度较大;在同一密封间隙下,随着压缩机叶轮入口流量...     

考虑间隙的压气机转子内部流动的数值模拟

采用时间推进法求解三维N-S方程，开发了一种用于计算考虑顶部间隙的压气机转子内部流场的三维粘性程序。对某压气机转子顶部间隙内的流动进行了详细的数值模拟，计算结果与试验结果吻合良好。通过分析可以发现，动叶顶部问隙的流动将引起叶片顶部气流的欠偏转，从而降低了转子附近相当大区域内的做功能力。同时，对于间隙内细微的流动结构也进行了较为深入的分析。     

半开式复合叶轮离心泵不同叶顶间隙的水力特性分析

 针对服务于航天低温循环系统的半开式复合叶轮离心泵效能利用率低的问题,研讨了其内流场在3种不同叶顶间隙下的工作情况。应用ANSYSY-Fluent软件对3种不同叶顶间隙的流场进行三维定常全流场数值模拟,得出3种叶顶间隙对离心泵内流特性的影响规律。通过对实物泵的水力特性试验以及试验结果与数值模拟结果对比分析,得出叶顶间隙是半开式离心泵存在能量损耗原因之一,减小叶顶间隙有利于提高效能利用率,并确认了试验数值模拟的可靠性。