反预旋密封动力特性实验研究

密封的动力特性对旋转机械转子系统稳定性影响较大,反预旋密封是提高密封稳定性的有效方法。本文设计加工了阻旋栅与反旋流密封,实验研究了反预旋密封动力特性,设计搭建反预旋密封动力特性实验台,应用不平衡同频激励法实验研究反预旋对密封动力特性的影响。研究结果表明,反预旋密封的动力特性绝对值随进出口压比与转速的增大而增大;反预旋装置可有效降低密封交叉刚度,增加密封主阻尼,提高密封稳定性。本文研究揭示了反预旋密封抑制气流激振力的机理,为设计反预旋密封提供理论依据。     

密封动力特性系数试验识别方法及影响因素分析

引入转子动力学双平面平衡理论,将多级密封内的分布气流力等效到气缸两个端面上,建立多级密封动力特性系数识别模型.该模型考虑气缸平动和偏摆混合运动情况,并通过共振的方法放大气流力影响,从而提高识别精度.构建密封动力特性试验台,研究进出口压比、转速、偏心、间隙等因素对密封动力特性系数的影响.试验结果表明,8个刚度阻尼系数随着进出口压比增大有明显增大,且垂直和水平方向存在耦合效应.随转速增大,交叉耦合刚度系数和直接阻尼系数随转速变大趋势明显,而直接刚度系数和交叉阻尼系数变化不很明显.偏心状态下的交叉耦合刚度系数比同心状态下变大,而直接阻尼系数则减小,说明转子在偏心状态下比同心状态下更容易失稳.随密封平均间隙变小,8个动力特性系数绝对值增大.     

新型涡流槽密封泄漏特性与动力特性研究

提出一种密封入口周向均匀设置有涡流槽的新型密封结构,建立了传统迷宫密封与新型涡流槽密封泄漏特性及动力特性求解模型,在实验验证数值计算方法准确性的基础上,通过比较分析了传统迷宫密封与新型涡流槽密封在不同进出口压比、预旋比工况下的泄漏特性与动力特性,研究了新型涡流槽结构对密封泄漏特性及动力特性的影响机理。研究结果表明：随着涡流槽数量的增加,涡流槽密封的泄漏量逐渐降低;在同一压比下,不同涡流槽数新型密封的泄漏量之间差值随着压比的增大而增大。当压比为6时,64涡流槽的新型密封较传统迷宫密封,泄漏量下降了3.37%;在高预旋比的工况下,不同涡流槽数量密封的切向气流力均与转子涡动方向相反,起到抑制转子涡动的作用,且随着涡流槽数量的增加,切向气流力也随着增大;随着转子涡动频率的增大,三种不同涡流槽数量密封的交叉刚度先减小到负值然后增大到正值。涡流槽密封的有效阻尼均高于传统迷宫密封,新型涡流槽密封可以提高转子系统的稳定性。     

进口预旋对高压迷宫密封流体激振转子动力特性的影响

采用基于转子多频椭圆涡动模型和动网格技术求解非定常Reynolds-Averaged Navier-Stokes(RANS)方程,研究进口预旋对高压环境下迷宫密封非定常流场和流体激振转子动力特性的影响。分析对比进口预旋比为0.2、0.5和0.7时迷宫密封腔室的旋流强度、周向压力和转子动力特性系数。研究结果表明:高压环境下迷宫密封在低预旋比0.2时具有正的、与频率无关的直接刚度系数;随进口预旋比增大,迷宫密封有效阻尼显著减小,穿越频率明显增大;当预旋比从0.5增加至0.7时,有效阻尼的穿越频率从39.1 Hz升高至55.4 Hz;进口预旋增加会使得密封腔室周向旋流强度增加和周向压力分布不均匀性显著增强,进而导致迷宫密封的直接刚度和交叉刚度Kxy增加,高频区(f30 Hz)下直接阻尼降低和有效阻尼明显降低。     

袋型阻尼密封动力特性数值与实验研究

通过非定常动网格技术，建立了袋型阻尼密封动力特性多频椭圆涡动求解模型，在实验验证求解模型准确性的基础上，研究了袋型阻尼密封腔室轴向长度、周向挡板数量及深度对密封动力特性的影响；并对不同周向挡板数量的等腔室袋型阻尼密封的泄漏特性进行实验研究。研究发现，密封腔室轴向长度为d=4/8mm的传统袋型阻尼密封比d=10mm的等腔室袋型阻尼密封的有效阻尼C_eff约增加21.5%；随着二次腔室轴向长度从d=10mm减小到d=6mm，有效阻尼C_eff约增加14.1%，流体压缩效应更加明显，增加了腔室内的动压，有利于抑制转子涡动。等腔室袋型阻尼密封的周向档板数量对其阻尼系数有显著影响，当涡动频率大于200Hz时，挡板数从24减少到4时，有效阻尼C_eff约增加37.8%，稳定性明显提高。当袋型阻尼密封空腔深度从3mm增加到6mm时，等腔室袋型阻尼密封的交叉刚度较大、C_eff约减小51.7%，稳定性降低。     

新型流线槽流体动压型机械密封性能*

以核主泵用新型流线槽流体动压机械密封为研究对象,建立密封间隙内液体膜的压力控制方程,应用有限差分法求解,分析特定工况下流线槽的结构参数对密封性能的影响。结果表明：泄漏量和刚度对密封间隙的变化最为敏感,间隙增大时,泄漏量迅速增加同时刚度急剧下降;刚度随槽深、槽长比、堰宽比增大而先增后减,并在一定区域获得峰值。流线槽槽数为12、槽深为2 μm、密封端面间隙为1 μm、槽长比为0.6、堰宽比为0.6时,液体膜具有较大的开启力、刚度和刚漏比,密封端面产生的流体动压效应显著,密封工作性能达到较佳状态。     

含有凹槽结构迷宫密封泄漏性能的数值研究

针对不同结构迷宫密封泄漏特性的问题,通过采用CFD三维分析的方法,研究了直通式和含有矩形和圆形凹槽的迷宫密封在不同压比,间隙,转速下的三维流场和泄漏特性。研究结果表明:含有凹槽的结构能够显著的加快耗散气体动能,进而提高密封效率,降低迷宫密封泄漏量,其中圆形凹槽比矩形凹槽阻止泄漏量更优;随着间隙增大,迷宫密封泄漏均增大,泄漏量和泄漏增长率依次是圆形优于矩形优于直通式;随着进出口压比的增大,泄漏量增加明显,矩形与圆形凹槽增加趋势相近;随着转速的增大,气体在迷宫密封内的湍动能耗散增大,泄漏量有所降低,凹槽迷宫密封内的涡旋充分耗散,泄漏量降低更多,达到极值后趋于稳定。     

基于FLUENT迷宫密封动力特性分析

利用CFD有限元软件Fluent计算迷宫密封三维流场,提出一种计算密封动力特性系数的方法,并研究了偏心率、入口预旋、涡动速度对转子密封动力特性的影响.计算结果表明:入口预旋是产生交叉刚度的主要原因,入口预旋越大交叉刚度越大;主刚度和交叉阻尼与偏心率的关系基本上是线性的,而交叉刚度和主阻尼随偏心率变化呈现明显的非线性.交叉刚度和主阻尼是影响密封转子系统稳定性的重要因素.     

考虑齿变形的迷宫密封泄漏特性流固耦合数值研究

为研究非金属热塑性材料的迷宫密封齿变形对密封性能的影响,建立考虑齿变形的迷宫密封泄漏特性瞬态流固耦合数值求解模型,在验证数值求解模型准确性的基础上,分析不同进出口压比下,酚酞聚芳醚酮(PEKC)、聚醚醚酮(PEEK)、聚醚砜酮(PPESKca30)3种材料的迷宫密封力学特性及泄漏特性。研究结果表明:考虑齿变形的密封流场中最后一节齿顶处的压力要低于其相同工况下未考虑齿变形的流体压力,而速度则恰好相反;在不同进出口压比下,密封齿受到气流力作用发生变形,密封径向间隙增大,导致泄漏量增加了6.6%~30%;当进出口压比相同时,材料的弹性模量越大,密封齿变形越小,封严性能越好;研究的3种材料中,PPESKca30的变形量最小,密封泄漏量最少;密封件最大变形量均出现在齿顶位置,且从其齿顶位置向齿根方向逐渐减小;密封件等效应力的最大值均分布在齿根位置,且从其齿顶位置向齿根方向逐渐增大。     

锥形间隙对袋型阻尼密封气流力影响机制研究

为探讨锥形间隙对袋型阻尼密封气流力的影响,建立锥形间隙袋型阻尼密封数值求解模型,研究进出口压比、偏心率、转速及锥形度对袋型阻尼密封气流力的影响;设计密封气流力实验台,分析在不同进出口压比及偏心率下锥形间隙袋型阻尼密封气流力的大小;通过密封压力分布规律揭示锥形间隙对袋型阻尼密封气流力的影响机制。研究结果表明:随着进出口压比,偏心率的增大,密封周向楔形间隙内流体动压效应增强,收敛间隙袋型阻尼密封与等间隙袋型阻尼密封的径向气流力增大,发散间隙袋型阻尼密封径向气流力绝对值增大。当转速为0时,密封切向气流力为0,随着转速的提高,密封的切向气流力逐渐增大,密封间隙内气流的周向流动是形成切向气流力的主要原因。收敛间隙袋型阻尼密封沿气流流动方向,密封径向间隙不断减小,气体的聚集使得密封腔中压力升高,径向压差增大,从而产生较大的径向气流力。     

可倾气封与固定气封性能试验比较分析

提出一种新型可倾气封。与传统固定式气封相比,可倾气封块在气流力作用下可以绕支点作自适应摆动,当气封块达到平衡位置时,切向激振力减小,从而提高稳定性。试验采用不平衡同频激励法测定可倾气封的动力特性,研究和比较了可倾气封和传统固定式气封的动静态性能。试验结果表明,两种气封泄漏量相当,可倾气封内产生的切向气流力比固定气封小。低压比下两种气封动力特性系数相近,随着压比的增大,动力特性系数差异逐渐增大。以气流力对气缸的做功量大小为综合评判依据,发现可倾气封做功量明显小于固定气封,压比越大,做功量差异也越大,可倾气封的稳定性较高。对于大型旋转机械而言,气封进出口压比很大,两种气封动力特性的差异将会更大。     

A novel negative dislocated seal and influential parameter analyses of static/rotordynamic characteristics

This paper proposes a new type of negative dislocated seal (NDS) based on the dislocated bearing theory to investigate the influential parameters of static rotor eccentricity and dislocated ratio on the static and rotordynamic characteristics of an example seal solved with computational fluid dynamics (CFD) the flow field. The rotordynamic characteristics of the NDS were investigated in respect of the effects of rotor whirling frequency on response force, stiffness coefficients, damping coefficients and rotor system stability, by multifrequency elliptical orbit rotor whirling model. Based on the studies, we reached the following conclusions. The circumferential pressure distribution of NDS and conventional labyrinth seal (LS) presents sine periodic variation approximately, while relative to the LS, the NDS has two divergent wedge gaps and reduces the hydrodynamic pressure effects, then the circumferential pressure difference and tangential force on rotor surface decreases by about 40 %~190 %. The leakage of the NDS linearly increases with the rising eccentricity ratio and dislocation ratio approximately, and is larger (about 0.9 %~1.5 %) than the LS. The direct stiffness coefficients of the two seals increase with the rise of rotor whirling frequency, while the absolute values of both the cross-coupled stiffness coefficients and the damping coefficients decrease with raising rotor whirling frequency. Compared with the LS, the NDS has smaller (about 28.8 %~206.2 %) cross-coupled stiffness coefficient, larger (about 26.15 %~60.39 %) effective damping coefficient, and good stability of rotor system. This study has developed a novel seal structure to improve the seal performance of turbomachinery such as aeroengine.     

An experimental identification model of rotordynamic coefficients of seals using unbalanced synchronous excitation method

This study presents an improved impedance method based on unbalanced synchronous excitation to identify the rotordynamic coefficients of labyrinth seals. The rotordynamic coefficient test is implemented near the cylinder resonance frequency to enlarge the influence of seal force. The force generated by the rotor unbalance is used to provide synchronous frequency excitation for the rotordynamic coefficient test. Four unique equations are set up under two sets of different rotor unbalance conditions to obtain four unknown complex rotordynamic coefficients. The factors that influence the rotordynamic coefficients of seals, namely, unbalance mass, inlet/outlet pressure ratio, and rotating speed, are considered. The dynamic coefficients are minimally affected by different rotor unbalances. The direct items are nearly equal with same signs, whereas the cross-coupled items are nearly equal with opposite signs. All coefficients increase with increasing inlet/outlet pressure ratio and rotating speed. The direct stiffness coefficients increase more quickly than the cross-coupled items. In addition, the effect stiffness and effect damping coefficients are analyzed; results indicate that both coefficients increase with increasing rotating speed.     

Test Results for Leakage and Rotordynamic Coefficients of Floating Ring Seals in a High-Pressure,High-Speed Turbopump

Test results are presented for short floating ring seals (D = 53.0 mm, L/D = 0.15) using a smooth surface and a round-hole pattern defined as a damper floating ring seal (h/C_r = 3, γ = 0.34: the ratio of hole area to surface area) for supplied pressures of 3.0, 5.0, and 7.0 MPa, respectively, with the shaft operating speed up to 24,800 rpm. The measured data includes leakage, attitude angle, eccentricity ratio, and rotordynamic coefficients such as stiffness, damping, and inertia. When the floating ring seals are locked up, the eccentricity ratio of the smooth surface floating ring seal is lower than that of the damper floating ring seal. The attitude angle increases linearly with the operating speeds. The damping coefficients of the damper floating ring seal are higher than those of the floating ring seal. Whirl frequency ratios of the floating ring seal are lower than the damper floating ring seal with high eccentricity ratio at low operating speed range. The design parameters determined from these test results will be used for high-pressure and high-speed turbopump seals in a liquid rocket engine system.     

Numerical prediction of rotordynamic coefficients for an annular-type plain-gas seal using 3D CFD analysis

Annular-type gas seals in many types of compressors and turbines are designed to reduce leakage and enhance the vibrational stability of the turbo machinery. Many researchers have attempted precise theoretical evaluation of the leakage and the rotordynamic coefficients from reaction forces of small seal gaps. The Bulk-flow model, which is based on Hirs’ lubrication equation, is a general method with advantages of simplicity and short computing time. However, due to the disadvantage of the long time required to develop analysis code, and constraints from complicated seal shapes, CFD analysis is currently preferred. In the present, the method for determining the rotordynamic coefficients of an annular plain-gas seal, which is the simplest shape of gas seals, is suggested by extending the analysis of an annular plain-pump seal. A relative coordinate system for steady-state simulation is defined to calculate the compressible flow field and dynamic pressure distribution of the seal gap. The present analysis is verified by comparison with results acquired from Bulk-flow analysis code and published experimental results. The 3D CFD rotordynamic coefficients results of direct stiffness(K) and cross coupled stiffness(k) show better improvements in prediction.     

Analysis of Multi-Land High Pressure Oil Seals

An analysis for the laminar/turbulent flow in high pressure oil ring seals is presented. A fully-developed bulk-flow model for low axial Reynolds numbers is introduced to predict the static and dynamic force response of multi-land oil seals. The model includes the effects of bearing surface roughness, variable seal clearances, fluid inertia and viscous loss effects at the inlet of the first land in a multi-land oil seal. Internal groove pressures in the seals are determined via a mass conservation algorithm with Reynolds condition at the cavitation inception zone. Predictions show that the viscosity effect at the seal inlet is minimal for turbulent flow across the seal. However, for laminar oil seals, the entrance loss viscous effect can substantially increase the direct stiffness. Load capacity and rotordynamic force coefficients for one-land, two-land and three-land seal examples are discussed in detail.     

迷宫气封三维非定常流场及转子动特性数值仿真

通过计算流体力学方法,采用近似的解析变换网格,以及混合有限分析格式,对迷宫气封流场进行三维非定常数值求解,进而求得密封气流对转子的气流激振力,获得转子的动特性系数。将计算结果与试验结果以及双控制体计算结果相比较,结果令人满意,说明了该计算程序是正确可靠的。该方法精度较高,适用范围广,可以应用于各种复杂的涡动情况及各种齿型,对气封转子的深入研究有重要意义。计算结果还显示了主刚度、主阻尼对气流进口周向速度不敏感,而交叉刚度对气流进口周向速度非常敏感。由于交叉刚度对转子的稳定性影响相当大,这一点是值得注意和利用的。     

A modeling of pump impeller shroud and wear-ring seal as a whole, and its application to the pump rotordynamics

A modeling methodology of pump impeller shroud and wear-ring seal as a whole has been developed to give its rotordynamic coefficients. In this work the governing equations are derived for the continuous flow path of the impeller shroud and wear-ring seal. Pressure loss at the discontinuity of the connecting point between the impeller shroud and the wear-ring seal is defined by utilizing a pressure loss coefficient obtained from experimental measurements. The governing equations are solved directly by using the known conditions at the inlet of the impeller shroud and the outlet of the wear-ring seal. A detailed rotordynamic analysis has been carried out on a 750 m-head fourteen-stage centrifugal pump system with the effects of the hydrodynamic forces of such as impeller shroud and wear-ring seals, balance piston, and interstage seals. Results have shown that the first critical speed obtained with all the seal effects is much higher than that obtained without those effects, and moreover that the system under consideration is unstable. Large cross coupled stiffness (k) of the impeller shroud and wear-ring seal has been suspected as the source of the problem. Design modifications of the impeller shroud and wear-ring seal geometry have been performed to decrease k and increase the direct damping(C). Finally, the design modifications have yielded a stable and well damped system.     

Prediction of leakage and rotordynamic coefficients for the circumferential-groove-pump seal using CFD analysis

The circumferential-groove seal is commonly used in various turbopumps to reduce leakage. The main goal of this paper is to develop the method of three-dimensional CFD analysis for determining leakage and rotordynamic coefficients of the circumferential-groove-pump seal. A relative coordinate system was defined for steady-state simulation to calculate the velocity and pressure distributions of the seal clearance at each rotor whirl speed. Instead of setting the inlet and outlet pressures as the boundary conditions in the three-dimensional CFD analysis, as it is more commonly done, we used the inlet velocity and outlet pressure obtained from a preliminary two-dimensional CFD analysis. For prediction leakage, the presented analysis shows improvement from the bulk-flow model analysis. For the prediction of rotordynamic coefficients of K, k and C, the presented analysis provides results in closer agreement with the experimental values than those of the bulk-flow model analysis at several rotor speeds.