MATCH-MODE METHOD AND ITS NUMERICAL SIMULATION FOR ROTOR-STATOR INTERACTION SOURCE MODES AND PROPAGATION MODES IN AN ANNULAR DUCT WITH MULTI-TREATMENTS

The suppressing design of the engine nacelle in an aircraft can benefit from the development of the prediction system for the sound fields in engine ducts which includes the prediction of the source generation and that of sound propagation in ducts. First, the acoustic match mode principle between the source modes of rotor stator interaction noise and the propagation modes is presented in this paper. Second, by utilizing this principle, the theoretical prediction method for rotor stator interaction noise generation and its propagation and attenuation in an annular duct with multi treatments is developed. That means that the prediction of sound propagation and attenuation in the segmented ducts might no longer completely depend on the in duct mode measurements, and the investigation on the sound propagation and attenuation in ducts can be accomplished not only by acoustic mode measurement, but also by making use of the source prediction to determine the source modes excited by rotor stator interaction. The effects of fan speed, blade/vane numbers, axial spacing between rotor and stator on the in duct sound attenuation and generated sound power level before and after ducts (also including the sound power level of blade passing frequency and its harmonics at the inlet of ducts) have been numerically calculated by using this prediction method. The reliability of this prediction method is verified by reasonable agreement between the predicted results with measured results in references. By analyzing the results of calculating cases, some reference criteria are provided for the engineering design of the suppressing engine nacelle.

Numerical simulation of unsteady interaction of centrifugal impeller with its diffuser using Lagrangian discrete vortex method

In this study, an advanced Lagrangian vortex- boundary element method is applied to simulate the unsteady impeller-diffuser interactions in a diffuser pump not only for design but also for off-design considerations. In velocity calculations based on the Biot-Savart law we do not have to grid large portions of the flow field and the calculation points are concentrated in the regions where vorticity is present. Lagrangian representation of the evolving vorticity field is well suited to moving boundaries. An integral pressure equation shows that the pressure distribution can be estimated directly from the instantaneous velocity and vorticity field. The numerical results are compared with the experimental data and the comparisons show that the method used in this study can provide us insight into the complicated unsteady impeller-diffuser interaction phenomena in a diffuser pump.

High-fidelity simulation of blade vortex interaction of helicopter rotor based upon TENO scheme

Numerical simulation methods for unsteady vortex field of helicopter rotor with high resolution and low dissipation TENO8-AA primitive variables reconstruction schemes are established based on moving-embedded grid and Navier-Stokes equations.Firstly,the Targeted Essentially Non-Oscillatory(TENO)scheme are developed by employing ENO-like candidate stencil selection strategy,and the candidate stencil is adopted with optimal weight in smooth region while it is discarded completely in discontinuous region,which reduces the dissipation and dispersion errors and approaches better spectral properties.Then,the aerodynamic characteristics of Helishape-7A model rotor in Blade Vortex Interaction(BVI)state and the flowfield of Lynx rotor in hover are simulated,which validates that the blade tip vortex trajectory with larger wake age and more details of vortex can be captured by TENO8-AA scheme with only a quarter of grid points and half time comparing to WENO-JS scheme.Moreover,the simulation accuracy of thrust coefficient is improved by up to 36%.Finally,the analyses for BVI and aeroacoustic characteristics of Operational Loads Survey(OLS)rotor are conducted,and the different forms of interaction mechanism are explored,such as oblique and parallel interactions.The results indicate that TENO scheme not only ensures the resolution of simulation in discontinuous region,but also minimizes the numerical dissipation in smooth region dominated by blade tip vortex.Therefore,the acoustic pressure peak prediction error of rotor in BVI state is significantly reduced to 5.6%and 0.8%at two microphone locations,respectively.

基于流固耦合的压气机转子叶片非同步振动分析

压气机转子叶片非同步振动是近年来发现的一类新气动弹性问题,表现为叶片振动频率与转频不同步且具有锁频现象,严重影响航空发动机的可靠性和运行安全,目前对其产生机理并不完全清楚.为了深入研究压气机内不稳定流动与叶片非同步振动之间的耦合机制,基于时间推进的方法建立了多级压气机转子叶片全环的双向流固耦合模型,数值研究了刚性叶片与非同步振动柔性叶片的非定常流场、气流激励频率和结构响应特征,揭示了压气机转子叶片非同步振动的流固耦合机制.结果表明:近失速工况下,转子叶尖吸力面径向分离涡的周期性脱落及再附过程是导致叶尖压力剧烈波动的主要原因,其3倍谐波激励频率与转子一阶弯曲固有频率接近,提供了叶片非同步振动的初始气流激励源.叶片非同步振动发生时,位移响应表现为等幅值的极限环特征,振动以一阶弯曲模态主导,径向分离涡产生的非整数倍气流激励频率及其谐波频率最终锁定为叶片一阶弯曲固有频率,非同步振动的运动胁迫使得相邻通道叶尖流场周向趋于一致.研究成果及对叶片非同步振动流固耦合机制的认识可为压气机内部不稳定流动诱发的叶片振动失效分析提供有益参考.

直升机小速度前飞状态下的振动机理研究

针对直升机在小速度前飞状态下振动偏大问题展开机理研究。采用自由尾迹模型计算小速度前飞状态下的旋翼桨涡干扰气动特征;推导了桨叶4自由度桨叶挥舞动力学结构有限元模型,以进行模态分析和结构参数影响分析;采用预定气动载荷法,建立桨叶挥舞动力学模型,分析桨叶结构动响应/载荷特征。研究结果表明,小速度状态下,气动载荷中桨涡干扰所致的频率为五倍旋翼转速的谐波成分是其振动问题的“外部”气动力源头;旋翼展向上根部大分布质量引起的惯性载荷是其振动问题的“内部”根源;两者的综合作用使得通过频率的旋翼动载荷高于基准旋翼,引起机体的异常振动。

抽水蓄能机组动静干涉与相位共振诱发振动故障机理及抑制方法研究

动静干涉与相位共振故障直接影响抽水蓄能电站水泵水轮机安全与稳定运行。本文以某水泵水轮机为对象,系统研究了由动静干涉产生的水力激振模式,并对其进行相位共振风险评估。通过实例计算分析了张河湾与黑麋峰抽水蓄能水泵水轮机由动静干涉引起厂房振动影响因素。同时,通过统计国内部分抽水蓄能电站水力参数,计算了动静干涉水力激振模式与相位共振风险系数RF,并提出相应预控措施。为其他大型抽水蓄能电站的振动问题提供参考,并为即将大规模建设的抽蓄电站安全稳定性提供积极借鉴意义。

长短叶片转轮动静干涉引起的水力激振模态数值分析

本文以5个长叶片和5个短叶片转轮(活动导叶数为16)为例,通过数值计算,分析了长短叶片转轮的动静干涉引起的水力激振模态问题。结果表明,长短叶片转轮动静干涉引起的水力激振模态比较复杂。在无叶区,水力激振模态“节径”数为相应倍频数,如5倍转频对应5“节径”等;在双叶栅区,激振力模态既有长(短)叶片数的特征(如15倍转频的模态的节径数为1),又有叶片总数的特征(如20倍转频的节径数为4,且模态旋转方向与转轮旋转方向相同)。本文的研究为长短叶片转轮的水泵水轮机的结构避振提供了新的方向。

宁海抽水蓄能电站机组相位共振风险评估

通过研究诱发相位共振的相关因素,消除抽水蓄能电站机组相位共振,提高抽蓄机组的运行稳定性,利用归纳分析法,从基础模型选择及模型试验对比结果、无叶区宽度比较、不同转轮叶片数与活动导叶数配比的水压脉动频率及优缺点、相位共振风险因子分析及业绩比较等几方面评估了宁海抽水蓄能电站机组由于动静干涉引起的相位共振风险。研究结果表明:宁海抽水蓄能电站基础模型选择合适,优化后模型各项稳定性指标优于基础模型;无叶区D_(0)/D_(1)=1.23属于国内抽蓄电站较高水平;10+16的转轮叶片数与活动导叶数配比合理,水压脉动频率较低;较低波速下相位共振风险因子高于国内工程经验值,但低于国外工程统计值。研究成果说明宁海抽水蓄能电站机组水力开发选型合理先进,发生相位共振风险较低,评估过程可为后续新建抽水蓄能电站评估提供一定参考和借鉴。

Numerical Simulation of Sand Erosion Phenomena in Rotor/Stator Interaction of Compressor

Sand erosion is a phenomenon where solid particles impinging to a wall cause serious mechanical damages to the wall surface. This phenomenon is a typical gas-particle two-phase turbulent flow and a multi-physics problem where the flow field, particle trajectory and wall deformation interact with each other. On the other hand, aircraft engines operating in a particulate environment are subjected to the performance and lifetime deterioration due to sand erosion. Especially, the compressor of the aircraft engines is severely damaged. The flow fields of the compressor have strongly three dimensional and unsteady natures. In order to estimate the deterioration due to sand erosion, the sand erosion simulation for a compressor is required under the consideration of the rotor-stator interaction. In the present study, we apply our three dimensional sand erosion prediction code to a single stage axial flow compressor. We numerically investigate the change of the flow field, the particle trajectories, and the eroded wall shape in the compressor, to clarify the effects of sand erosion in the compressor.

Unsteady Rotor-Stator Interaction in High Speed Compressor and Turbine Stages

The blade row interaction can alter the time-mean flow and therefore be of interest for aerodynamic design analysis. Whereas results within low subsonic turbomachines are quite numerous in the literature, there have been far fewer works which give results of blade row interaction within high speed cases. Two cases are related in this paper. First, the effects of an incoming wake on the rotor flow field of a transonic compressor are analyzed. The blade row interaction proved to be positive regarding the total pressure ratio, but negative regarding the losses. The second case concerns a transonic turbine. Particular emphasis is placed on the assessment of the deterministic correlations included in the Averaged Passage Equation System.

Experimental Analysis of the Rotor Stator Interaction Within a High Pressure Centrifugal Compressor

An analysis of the experimental results obtained by laser two focus anemometry in the rotor-stator inter-row region of a high-speed high-pressure centrifugal compressor is presented with the aim of quantifying the unsteady effects of the rotor-stator interaction. Two complementary methods are used. First, the results are analyzed in terms of the time-averaging procedure developed by Adamczyk. The purely time dependent correlations of the velocity components are quantified. They show that the unsteady interaction is mainly due to the splitter wake-vane interaction. Then, it is shown that the rotor-stator interaction produces spatial harmonics which are identified as spinning modes by means of Fourier series.

Laser Measurements in High Speed Compressors for Rotor-Stator Interaction Analysis

This paper deals with the experimental quantification of the unsteady effects of the interactions between rotor and stator rows in high speed compressors. Due to the fact that the levels of the periodic fluctuations arising from the unsteady interaction may be low compared with the random fluctuations arising from the measurement uncertainties, it is crucial to minimize the errors inherent to the used technique. The first part of the paper concentrates on technical details relative to the experimental process. The second part is devoted to the data post-processing. Two tools for analysing the rotor-stator interactions are presented. The first tool is based on a decomposition of the flow field which was initially introduced to solve numerical problems when attempting to calculate the flow field in a multi-row configuration. The second tool is based on a spectral analysis of the signal, that qualifies the interaction in a sense of circumferential spinning lobes. Experimental results obtained within both an axial and a centrifugal high speed compressors are used to illustrate the data processing. In both cases, the effects of the unsteady interaction are quantified.

Numerical Simulation of Rotor-stator Interactions in a Transonic Compressor Stage

A numerical method is developed for the simulation of rotor\|stator interactions in a compessor or turbine stage. This method solves quasi\|three\|dimensional Navier\|Stokes equations by an implicit high\|resolution finite volume approach.A fully conservative method is designed to compute the inviscid and viscous fluxes at the interface of rotor and stator grids. Numerical results of rotor\|stator interactions in a transonic compressor stage are presented. The mechanism of rotor\|stator interactions in this compressor stage is discussed in terms of the computational results.

An Extraction of the Dominant Rotor-Stator Interaction Modes by the Use of Proper Orthogonal Decomposition (POD)

The Proper Orthogonal Decomposition method is applied to the instantaneous velocity field within the rotor-stator inter-row region of a high-speed high-pressure centrifugal compressor. The processed data come from experiments and numerical simulations. In comparison with a Fourier transform, the POD gives the best modal approximation for both initial fields, in terms of the energy expressed on any given number of modes to be taken into account： to reach 98% of the total energy of the velocity field, the required number of POD modes is around nine times smaller than the number of Fourier harmonics. The individual POD modes are given and show that the unsteady rotor-stator interaction is already present in the very first modes.

Unsteady Flow Variability Driven by Rotor-stator Interaction at Rotor Exit

Numerical investigation of the unsteady flow variability driven by rotorstator interaction in a transonic axial compressor is performed. Two models with close and far axial gap between rotor and stator rows are studied in the simulation. Particular attention is attached to the analysis of mechanisms involved in driving rotor wake oscillation, rotor wake skewing and flow angle fluctuation at rotor exit. The results show that smaller axial gap is favorable to enhance the interaction in the region between two adjacent rows, and the fluctuation of the static pressure difference between two sides of rotor wake is improved by potential field from down stator, which is the driving force for rotor wake oscillation. The interaction between rotor and stator is weakened by increasing axial distance, rotor wake shifts to suction side of rotor blade with 5%-10% of rotor pitch, the absolute value of flow angle at rotor exit is less than that in the case of close interspace for every time step, and the fluctuation amplitude is also decreased.

Theoretical and Numerical Analysis of the Mechanical Erosion in Steam Turbine Blades. Part I

The methodology of calculation of the velocity distribution for the stream frictionless and the drops in the flow line, on the basis of the frictionless, two-dimensional, stationary, transonic and homogenous flow is established. The knowledge of conditions that govern the low pressure section of steam turbines in the last stage to have an approximate movement of the droplets in the blade cascades and the accumulation of droplets on the stator blades, flowing through the steam, is presented. This study is used for developing a code in Fortran about the velocity distribution in the output of stator blades that have flow conditions of wet steam, in order to understand the causes that originate the erosion on the blades of the last stages in the low pressure section of steam turbines.

旋翼桨-涡干扰噪声特性风洞试验研究

在中国航空工业空气动力研究院FL–10风洞中开展了旋翼桨–涡干扰噪声传播特性试验,对BO–105主旋翼40%缩比模型中等前飞速度爬升、平飞、斜下降状态的气动噪声进行了测量。首先采用Heyson洞壁干扰修正方法确定风洞试验时的旋翼下滑角,通过气流内测量阵列移动获得了桨盘平面下方完整的噪声辐射场,然后对不同飞行状态下的桨–涡干扰噪声传播特性进行了分析,得到了典型状态的声压–时间历程、频谱和声压级云图。结果表明:旋翼斜下降飞行状态出现了明显的桨–涡干扰噪声,干扰较强时桨叶前行侧和后行侧都会产生桨–涡干扰噪声,且其传播具有明显的方向性,即前行侧指向桨盘上游和桨盘下方,后行侧指向桨盘下游。

泵喷定子襟翼作动对转子非定常力抑制方法数值研究

[目的]转子非定常力是泵喷推进器轴系振动的主要激励源,其产生机理和抑制机理受转−定子干扰流动的影响,需研究其抑制方法。[方法]在泵喷推进器定子后缘引入襟翼结构,利用襟翼作动产生二次流动,改变转子入流条件,调控转−定子干扰流动,达到抑制转子非定常力的目的。以具有前置定子襟翼的Suboff全附体艇后泵喷推进器为研究对象,采用基于SST k–ω湍流模型的URANS方法和动网格技术建立可实现定子襟翼作动的数值模型。针对转子非定常力转子叶频分量的抑制,给出定子襟翼作动规律的表达式。[结果]结果显示,在襟翼作动最优控制下,泵喷的水动力性能变化不超过1%,转子轴向非定常力在转子叶频处下降了83.35%,单个转子叶片轴向非定常力在转子叶频处降低了81.80%;襟翼作动对定子尾迹与转子入流速度的调控是抑制转子非定常力的机理。[结论]研究表明,最优控制下的定子襟翼作动能够在保持水动力性能的同时使转子非定常力特征线谱得到显著抑制,可为泵喷推进器的叶频等线谱控制提供一种新的思路。

叶片出口梯形切割对离心泵蜗壳流激噪声影响的研究

为探究叶片出口梯形切割对离心泵蜗壳流激噪声的影响,以一台比转速为66的单级单吸离心泵为对象,通过定义切割宽度系数δ与径向高度系数γ,设计了9种切割方案。基于RNG k-ε湍流模型对离心泵进行全三维非定常数值模拟,在此基础上采用边界元法(boundary element method,BEM)计算内场噪声,采用结构有限元法(finite element method,FEM)耦合声学边界元方法计算外场流激噪声;分析不同切割方案下离心泵水力特性和噪声幅射特性,经试验方法验证数值计算的准确性。研究表明:动静干涉是离心泵蜗壳流激噪声产生的主要原因,合理的叶片出口梯形切割能使离心泵水力性能基本稳定的同时有效降低动静干涉强度及蜗壳流激噪声水平;声学性能最优切割方案,叶频处的进、出口监测点声压级分别下降13%和7.5%,外场噪声监测点声压级下降2.4%。

满负荷工况下水泵水轮机动静干涉效应研究

动静干涉引起的压力脉动主要是叶片通过频率及其倍频。这些频率的压力脉动在无叶区、活动导叶和固定导叶以及流道上游传播和反射,极大地影响机组的安全稳定运行。本文基于可压缩计算方法,获得某高水头水泵水轮机满负荷工况下1倍和2倍叶片通过频率压力脉动,通过分析其幅值和相位的分布特征,探索了压力脉动传播特性。