Numerical Study on the Duct Noise Control of Single-Stage Axial Flow Fan with Wave Leading Edge Stator Blade Configurations

This study focuses on a single-stage axial flow fan, investigating the effect of three kinds of wave leading edge stator blades on its noise reduction. The DDES method and the duct acoustic analogy theory based on the penetrable data surface were used for noise prediction. The results showed that the three kinds of wave leading edge blades were effective in reducing the rotor-stator interaction tonal noise and also have a certain inhibitory effect on broadband noise. The A10W15 stator blade can effectively reduce broadband noise in the frequency range of 2200 - 4200 Hz. When the amplitude is increased to 20, the noise reduction effect is further enhanced. However, when the amplitude is increased to 30, the broadband noise reduction effect is no longer significant. Further research shows that the wave leading edge stator blades can significantly change the pressure fluctuation distribution on the leading edge and suction surface, which control the modal energy distribution. Finally, this paper analyzed multiple factors affecting the broadband noise reduction, such as the noise source cut-off and cut-on effect and correlation. The purpose of this paper is to explore the laws of the influence of wave leading edge blades on the duct noise of real fan, and to reveal its noise control mechanism. .

Heat Transfer and Flow Structure of a Turbine Blade's Air-cooled Leading Edge Considering Different Hole Shapes and Additional Flow Angles

A numerical study is conducted to elucidate the impact of hole shapes and additional flow angles on the flow structure of the coolant and temperature field in the leading edge area of the gas turbine rotor.Four typical hole shapes are considered for the GE-E3 blade.The impact of the additional flow angle(E)within each hole shape on the temperature field is investigated.The results indicate that for the leading edge area and suction surface,the fan-shaped hole case performs best in decreasing temperatures,with a decrease of about 43 K.This is mainly due to the fact that the fan-shaped hole has the maximum expansion in hole spanwise direction.For the pressure surface,the console hole case performs best in decreasing temperatures,with a maximum reduction of about 47.2 K.The influence of E on the surface temperature at leading edge area varied between the different hole shapes.For the cylinder hole and console hole,the E=-20°case has the lowest area-averaged temperature.Because both the fan-shaped hole and the 7-7-7 shaped hole are expansion holes,the pattern of variation of the leading edge area temperature with increasing E is similar for the fan-shaped hole case and 7-7-7 shaped hole case.The E=20°case shows the lowest spanwise-averaged temperature near the hole outlet,and the E=-20°case shows the lowest spanwise-averaged temperature further downstream.

Experimental Investigation on the Adiabatic Film Effectiveness for Counter-Inclined Simple and Laid-Back Film-Holes of Leading Edge

The adiabatic film effectivenessηof the counter-inclined film-holes fed by varying internal coolant intake on the turbine vane leading edge model was experimentally investigated.A semi-cylinder model was adopted to model the vane leading edge which was arranged with two-row holes,which located at±15°on both sides.The four Leading edge model with the combinations of hole-shape(simple holes and laid-back holes)and intake structure(plenum and impingement)were tested under four blowing ratios M of 0.5,1.0,1.5,and 2.0.Theηcontours were obtained by the transient measurement technique based on double thermochromic liquid-crystals.The results present that theηis sensitive to the M for the four studied leading edge cases.The addition of impingement enhances theηfor the two studied holes.The film jets make the coolant-flow closed to the target surface,resulting in higherηunder lower M.The core with higherηappears in the downstream area of hole-exit.Theηenhancement can be provided to almost the identical level by adding the impingement-holes and improving the hole-exit shaping in most areas.With increasing M,the jets with stronger exit normal momentum penetrate into the main-flow.The impingement addition may be a more effective program to upgrade theηrelatively to the exit shaping under larger M.Besides,the laid-back holes with impingement case produce the highest film cooling performance among the four cases,providing great potential in the leading edge especially under larger M.

An experimental investigation on the trailing edge cooling of turbine blades

An experimental study was conducted to quantify the flow characteristics of the wall jets pertinent to trailing edge cooling of turbine blades.A high-resolution stereoscopic particle image velocimetry(PIV)system was used to conduct detailed flow field measurements to quantitatively visualize the evolution of the unsteady vortices and turbulent flow structures in the cooling wall jet streams and to quantify the dynamic mixing process between the cooling jet stream and the mainstream flows.The detailed flow field measurements were correlated with the adiabatic cooling effectiveness maps measured by using pressure sensitive paint(PSP)technique to elucidate underlying physics in order to explore/optimize design paradigms for improved cooling effectiveness to protect the critical portions of turbine blades from harsh environments.

Investigation of film cooling on the leading edge of turbine blade based on detached eddy simulation

In order to assess the influences of curved hole passage on cooling effectiveness and flow structure of turbine blade leading edge,the detached eddy simulation is applied to numerically investigate the AGTB turbine cascade under the condition of global blowing ratio M=0.7.The straight or curved cooling holes are located at either the pressure or suction side near the leading edge.The analysis and discussion focus on the local turbulence structure;influence of pressure gradient on the structure,and distribution of cooling effectiveness on the blade surface.The numerical results show that cooling hole with curved passage could bring positive impact on the increase of the local cooling effectiveness.On the suction side,the increased cooling effectiveness could be about 82% and about 77% on the pressure side,compared to the conventional straight hole.

Aerodynamics and Flight Dynamics of Free-Falling Ash Seeds

Samaras or winged seeds spread themselves by wind. Ash seed, unlike other samaras, has a high aspect ratio wing which can generate enough lift force to slow down descent by rotating about the vertical axis and spinning around its wing span axis simultaneously. This unique kinematics and inherent fluid mechanism are definitely of great interest. Detailed kinematics of free falling ash seeds were measured using high-speed cameras, then corresponding aerodynamic forces and moments were calculated employing computational fluid dynamics. The results show that both rotating and spinning directions are in the same side and the spinning angular velocity is about 6 times of rotating speed. The terminal descending velocity and cone angles are similar to other samaras. Analysis of the forces and moments shows that the lift is enough to balance the weight and the vertical rotation results from a processional motion of total angular moment because the spin-cycle-averaged aer-odynamic moment is perpendicular to the total angular moment and can only change its direction but maintain its magnitude, which is very similar to a spinning top in processional motion except that the total angular moment of ash seed is not along the spin axis but almost normal to it. The flow structures show that both leading and trailing edge vortices contribute to lift generation and the spanwise spinning results in an augmentation of the lift, implying that ash seeds with high aspect ratio wing may evolve in a different way in utilizing fluid mechanisms to facilitate dispersal.

Method for utilizing PIV to investigate high curvature and acceleration boundary layer flows around the compressor blade leading edge

Particle Image Velocimetry(PIV)is a well-developed and contactless technique in experimental fluid mechanics,but the strong velocity gradient and streamline curvature near the wall substantially limits its accuracy improvement.This paper presents a data processing procedure combining conventional PIV and newly developed Mirror Interchange(MI)based Interface-PIV for the measurement of the boundary layer parameter development in the blade leading edge region.The synthetic particle images are used to analyze the measurement errors in the entire procedure.Overall,three types of errors,namely the errors caused by the Window Deformation Iterative Multigrid(WIDIM)algorithm,the discrete data interpolation and integration,and the wall offset uncertainty,comprise the main measurement error.Specifically,the errors due to the discrete data interpolation and integration and the WIDIM algorithm comprise the mean bias,which can be corrected through the error analysis method proposed in the present work.Meanwhile,the errors due to the WIDIM algorithm and the wall offset uncertainty contribute to the measurement uncertainty.Computational fluid dynamics-based synthetic particle flows were generated to verify the newly developed PIV data processing procedure and the corresponding error analysis method.Results showed that the data processing method could improve the accuracy of PIV measurements for boundary layer flows with high curvature and acceleration and even with significant flow separation bubbles.Finally,the data processing method is also applied in a PIV experiment to investigate the boundary layer flows around a compressor blade leading edge,and several credible boundary flow parameters were obtained.

钛合金包边复合材料风扇叶片的鸟撞数值仿真

为降低鸟体撞击航空发动机中带钛合金包边树脂基复合材料风扇叶片的试验成本,开展了数值仿真研究,为钛合金包边在航空发动机风扇叶片上的应用提供参考和依据。对风扇叶片进行简化,采用ABAQUS有限元软件构建了鸟撞带钛合金包边和不带钛合金包边的风扇叶片模型,其中,钛合金包边和复合材料叶片之间用粘结界面单元进行粘接,研究了不同鸟体冲击角度和速度下2种风扇叶片的损伤。结果表明:在鸟体冲击速度相同时,随着冲击角度的增大,风扇叶片的损伤增大且能量吸收率提高,在冲击角度也相同时,带钛合金包边的风扇叶片损伤更小且能量吸收率更高;在鸟体冲击角度相同时,随着冲击速度的加快,风扇叶片的损伤增大且能量吸收率提高;在鸟体冲击下,粘结界面单元最终发生拉伸破坏,在低速度冲击下还会发生剪切损伤。

大型风力机叶片前缘的雨滴冲击动力学响应机制

随着近年海上风力机设计的大型化,叶片前缘的雨蚀失效问题变得愈发突出,不仅影响机组的风能转化效率,对结构的稳定运行也构成潜在威胁。采用光滑粒子流体动力学(smooth particle hydrodynamics,SPH)法研究雨滴内部的本构关系,以有限元法(finite element method,FEM)建立叶片前缘的代表性体积单元(representative volume element,RVE)模型,两者相互耦合,研究雨滴在叶片表面形成的冲击响应过程。考虑自然降雨的实际工况,建立与降雨强度相关联的雨滴尺寸模型,以及雨滴的空间分布模型;通过单雨滴的冲击仿真,研究叶片表面冲击载荷以及雨滴内部的速度分布,从而解构雨滴冲击的物理过程,并通过冲击的应力、应变场分析,为潜在损伤区提供评价;建立多雨滴冲击的仿真模型,研究冲击应力场之间的耦合作用以及涂层表面的塑性应变累积效果。研究结果表明,水锤冲击是造成塑性应变累积的关键因素,虽然横向喷射阶段的应力响应幅值小并呈现一定的无序特征,但如果存在多雨滴耦合冲击的情况,则会在耦合区内出现应力峰值,并对叶片变形和失效存在潜在影响。

多参数变弯度翼型气动优化设计方法

为了获得机翼最优的气动外形,提出了一种多偏转参数与非均匀B样条结合的翼型前后缘连续偏转变形方法。以NACA3412翼型为研究实例,对翼型曲线进行参数化重构。以翼型前、后缘偏转位置和偏转角度为变化参数,模拟分析了不同变形状态对翼型气动特性的影响规律。以翼型升力系数和升阻比为优化目标,以前、后缘的偏转角度、偏转位置以及过渡段长度等六个偏转参数为设计变量,采用多目标遗传算法和ANSYS软件进行优化设计。结果表明,与基础翼型相比,优化后的变弯度翼型的升阻比提升约19.26%,升力提升约44.43%,明显改善了翼型的气动性能。

Numerical Analysis and PIV Measurements of Tip Vortex in an Axial Rotor with Skewed-Swept Blade at Its Leading Edge

Based on the characteristics of axial fans of outdoor units of centralized air-conditioners, using the finite-volume method, applying three-dimensional steady Reynolds-averaged Navier-Stokes equations coupled with Spalart-Allmaras turbulence model equation, and adopting SIMPLE algorithm, numerical analysis is made and applied to analyze the internal flow field of axial rotors with skewed-swept blade at its leading edge. This numerical simulation mainly investigates the formation and development of the tip vortex. Based on the tip vortex characteristics that have been captured, the internal flow numerical results are compared with those obtained by the PIV experiments. This comparison indicates a good agreement between numerical results and PIV results, thus proving the validity of the numerical simulation. In addition, based on the internal flow analyses of the axial rotor with skewed-swept blade at its leading edge, different flow phenomena features are presented. These flow features can be used for further improvements of the present rotor performance characteristics.

电火花成型电极修整航空发动机叶片的加工误差分析

针对航空发动机叶片电解加工后前后缘存在较大加工误差这一问题,采用电火花加工技术对叶片前后缘进行修整,并分析前后缘的加工误差。使用自研的六轴电火花成型机床,采用成型电极对叶片后缘进行修整加工,并利用三坐标测量机完成叶片点云数据的测量。采用遗传算法和迭代最近点算法,完成包络加工后叶片点云数据与理论模型的配准,通过最小二乘椭圆以及NURBS曲线拟合处理点云数据。针对拟合的叶片加工后轮廓曲线,通过在该曲线上等间距取点并计算这些点到叶片理论轮廓线的距离来反映叶片后缘的加工误差和加工误差的整体趋势。结果显示:经过电火花成型电极修整后叶片后缘的面轮廓度误差在-16.4~88.5μm之间,平均误差为53.7μm,叶片后缘的缘头处轮廓度误差最小,验证了电火花加工技术包络修整叶片前后缘的可行性。

零质量射流下波浪前缘叶片气动性能数值研究

针对垂直轴风机叶片大攻角工况下因流动分离导致的失速及颤振抖振问题,引入零质量射流激励对波浪型前缘叶片进行流动分离控制.采用大涡模拟方法建立了波浪前缘叶片绕流数值模型,探究了主/被动耦合控制下叶片升阻力特性及其流动分离机理,分析了射流参数(射流位置、动量系数)对波浪前缘叶片气动性能及失速特性的影响机制,研究发现:受控前后大攻角下波浪型前缘能诱导产生较小尺度流向涡,降低后方大分离涡尺度,波浪前缘与零质量射流耦合控制对于大攻角下流动分离抑制较单一控制更优;零质量射流吹气时使前缘流向涡有更高的动能抵抗逆压梯度从而延迟流动分离,吸气时会吸走流向涡的低动量流体,抑制流向涡发展成大分离涡;射流布置在距基准前缘0.033c处,即位于前缘流向涡最前端,能最大程度地参与前缘流向涡的生成,升阻比的提升效果最好;且升阻比提升量随着动量系数增大而增大,但控制经济性在动量系数0.018时最优,研究结果为垂直轴风力机失速控制提供了有益参考.

激光冲击强化对外物损伤叶片前缘的疲劳强度影响研究

为研究激光冲击强化对某型离心叶轮外物损伤后疲劳强度的影响,设计了反映真实叶片前缘部位的特征模拟件,并结合空气炮法模拟外物损伤,对比有/无激光冲击强化模拟件的高周疲劳试验结果,发现经激光冲击强化处理后,模拟件的疲劳强度提高约37%。同时,开展了激光冲击强化以及外物损伤后的残余应力/应变场数值仿真,结合Kitagawa-Takahashi(K-T)图法建立了考虑外物损伤与激光冲击强化的疲劳强度预测方法,与试验结果相比平均误差为7.3%,验证了方法的有效性。

基于SODIX方法的叶片前缘噪声指向性及降噪实验研究

以NACA 65(12)–10独立基准叶片为对象,使用线性传声器阵列和SODIX(SOurce DIrectivity modeling in the cross-spectral matriX)方法对基准叶片前缘噪声指向性分布特征及波浪前缘对叶片前缘噪声的影响进行了实验研究。开发了SODIX数据处理程序并进行了数值仿真验证,结果表明:不同指向角下计算结果的最大误差不超过0.26 dB。在半消声室内,利用由31个传声器组成的非均匀分布优化阵列,对NACA 65(12)–10独立基准叶片和仿生学叶片的前缘噪声开展了参数化声学实验。结果表明:在40°~142°指向角测量范围内,基准叶片前缘噪声指向性符合典型偶极子声源特征,峰值在130°指向角附近;随着频率升高,基准叶片前缘噪声指向性产生了显著的“波瓣”现象,频率越高,“波瓣”越多。进一步研究表明:不同波长和幅值的前缘构型都可以有效降低指向角测量范围内的前缘噪声;与波浪前缘的波长相比,波浪前缘的幅值对前缘噪声的影响更为显著,特别是在90°~120°指向角范围内,A30W20叶型的降噪量可达7.71 dB。

叶片不同切割形状对离心泵各项性能的影响

离心泵叶片直接影响离心泵的效率与使用寿命,因此,对叶片形状进行研究具有重要意义。对离心泵叶片出口边进行单一切割以改变离心泵性能,在此基础上,对叶片前缘、尾缘进行了双向切割,研究了不同切割形状对离心泵各项性能的影响。首先,以一台n_(s)=73的离心泵作为研究对象,使用UG软件进行了离心泵三维建模与叶片切割(切割出了24种叶片模型);然后,使用ICEM软件划分了网格,选用标准k-ε湍流模型作为计算模型,在离心泵叶片与蜗壳隔舌处设置了监测点;最后,采用ANSYS CFX软件,对无切割和切割后的模型进行了离心泵数值模拟计算,得到了离心泵在0.6Q_(d)~1.4Q_(d)工况下的外特性曲线;在外特性良好的前提下,研究了其内部流动结构、压力脉动特性,以及湍动能分布。研究结果表明:在1.0Q_(d)设计工况下,切割后的模型较无切割模型的效率均提升了4%左右,对称切割的模型中前缘为椭圆、尾缘为钝形的模型7的效率提升最高,提升了4.8%,非对称切割前缘为圆形、尾缘为背面半切割的模型14效率提升了5.4%;无切割模型内部流线紊乱且内部相对速度高的区域较多,非对称切割的模型14叶轮内部流线分布均匀且相对速度值和分布区域减小;相对于无切割模型,切割后的模型内部压力升高,对称切割的模型7压力脉动减小了10%,而非对称切割的模型14压力脉动强度增加了近30%;切割后的模型湍动能分布明显改善,尾缘处湍动能值减小,对称切割的模型7湍动能随时间变化而变化不大,表现更稳定。综合不同切割模型的外特性及稳定性表现可知,将前缘切割为椭圆、尾缘切割为钝形,能有效提升离心泵的性能。

Design and validation of a variable camber wing structure

Variable camber wing technology is one of the important development trends of green aviation at present.Through smooth,seamless,continuous and adaptive change of wing camber,the aerodynamic performance is improved in achieving increase in lift and reduction in resistance and noise.Based on the aerodynamic validation model CAE-AVM,Chinese Aeronautical Establishment(CAE)has carried out the design and validation of a variable camber wing,proposed an aerodynamic deformation matrix for the leading and trailing edges of aircraft wings in takeoff,landing and cruise conditions.Various structures and driving schemes are compared,and several key technology problems of leading and trailing edge deformation are solved.A full-size leading edge wind tunnel test piece with a span of 2.7 m and a trailing edge ground function test piece are developed.The deformation and shape maintenance capabilities of the leading edge is verified under real wind load conditions,and the load bearing and deformation capabilities of the trailing edge is verified under simulated follow-on load.The results indicate that the leading and trailing edges of the variable camber wing can achieve the required deformation angle and have a certain load-bearing capacity.Our study can provide some insights into the application of variable camber wing technology for civil aircraft.

Fast prediction of rain erosion in wind turbine blades using a data-based computational tool

Wind turbines(WTs)face a high risk of failure due to environmental factors like erosion,particularly in high-precipitation areas and offshore scenarios.In this paper we introduce a novel computational tool for the fast prediction of rain erosion damage on WT blades that is useful in operation and maintenance decision making tasks.The approach is as follows:Pseudo-Direct Numerical Simulation(P-DNS)simulations of the droplet-laden flow around the blade section profile are employed to build a high-fidelity data set of impact statistics for potential operating conditions.Using this database as training data,a machine learning-based surrogate model provides the feature of the impact pattern over the 2-D section for given wind and rain conditions.With this information,a fatigue-based model estimates the remaining lifetime and erosion damage for both homogeneous and coating-substrate blade materials.This prediction is done by quantifying the accumulated droplet impact energy and evaluating operative conditions over time periods for which the weather at the installation site is known.In this work,we describe the modules that compose the prediction method,namely the database creation,the training of the surrogate model and their coupling to build the prediction tool.Then,the method is applied to predict the remaining lifetime and erosion damage to the blade sections of a reference WT.To evaluate the reliability of the tool,several site locations(offshore,coastal,and inland),the coating material and the coating thickness of the blade are investigated.In few minutes we are able to estimate erosion after many years of operation.The results are in good agreement with field observations,showing the promise of the new rain erosion prediction approach.

后缘调整片对桨叶翼型气动特性的影响

直升机桨叶失速颤振后更容易引起旋翼操纵载荷的突增,为此提出增加桨叶后缘调整片的方案。以直升机常用桨叶翼型为基准翼型,通过求解雷诺平均Navier-Stokes方程模拟翼型气动特性,离散格式采用二阶迎风格式,湍流模型选择Spalart-Allmaras模型,并通过风洞试验结果验证了计算的准确度。分析了后缘调整片弯折角对翼型升力系数、阻力系数、力矩系数、升阻比等气动特性参数的影响。数值结果表明:随着后缘调整片弯折角的增加,翼型的升力系数和升阻比增加,零升攻角和失速攻角减小;在小攻角范围内,后缘调整片对翼型的阻力系数影响不大;后缘调整片弯折角的增加使得翼型的气动中心和焦点后移,但是会增加翼型的低头力矩。

叶片进排气边电解加工垂直供液流场特性研究

进排气边是航空发动机叶片中的重要功能部位,对加工精度有极其严苛的要求。针对某型航空发动机叶片,建立叶片进排气边的阴极三维模型和进排气边电解加工垂直供液的流场模型。采用COMSOL Multiphysics软件模拟进排气边电解加工过程,取不同加工间隙和不同进液口压力为因变量,研究垂直供液电解加工过程中的流场变化规律。实验结果表明,加工时电解液流速与进液口压力呈正相关;在相同电解液压力下,小加工间隙的流场分布比大加工间隙均匀。