Influence of the shape of the blade tip on the emitted noise in the air-gap between the rotor and the housing of an axial fan

The paper presents influence of the rotor blade tip shape of an axial fan on the emitted noise and on its aerodynamic characteristic. Appropriate measurements were first performed on the integral level of the same rotor with the two blade tip shapes: blade tip configuration A where the blade tip has the form of the prolonged basic blade, and configuration B with the winglet where the tip was slightly pushed towards the suction side of the blade. Moreover results of local pressure and sound pressure measurements in the area of the air gap made possible detailed analysis of the avarage pressure distribution and its time variance. The results showed strong dependence of the blade tip design on the emitted noise distribution, whereas changes of the aerodynamic characteristic with both tip designs were hardly noticed. The correlation between the emitted sound power level of the fan and the air pressure variance enabled to locate mechanism and origin of the noise generation in the zone between two consecutive rotor blades.     

后缘小翼智能旋翼减振效果影响因素分析

建立了带后缘小翼智能旋翼气动弹性载荷计算模型及减振优化分析方法。模型考虑刚体后缘小翼的气动力与惯性力对弹性桨叶系统的影响,使用粘性涡粒子法结合翼型查表法计算旋翼气动载荷,采用力积分法计算桨叶与桨毂载荷,构造了包含桨叶根部扭转及桨毂振动载荷为目标函数的优化问题,基于最速下降-黄金分割组合优化算法寻找最佳小翼偏转规律。研究发现,建立的后缘小翼载荷控制方法有效,可降低振动目标函数70%。桨叶的弹性扭转使后缘小翼能有效实施减振,但弹性扭转对小翼气动力矩的放大作用使减振时通常伴随着桨叶扭转载荷增大的现象。     

多翼离心风机气动噪声计算与降噪设计研究

以船用空调通风系统中多翼离心式风机为对象,建立风机内部流体三维建模,采用CFD软件进行稳态与非稳态计算.将得到的风机内部流场结果导入LMS Virtual.Lab声学软件中进行噪声预估,同时与实验结果对比,验证风机气动噪声计算的准确性.根据分析得知,风机气动噪声主要噪声源位于叶轮处并且与其内部流场分布和自身结构密切相关...     

带尾缘吹气的空心叶轮轴流式风机内部流动和气动噪声模拟

对带尾缘吹气的空心叶轮轴流式风机内部流动和气动噪声进行数值模拟计算,并从流动性能和噪声水平2个方面将之与原型风机进行对比分析。结果表明：两者的流动性能差别甚小,但在设计工况附近,空心叶轮风扇的气动噪声明显低于原型风扇。研究结果可为空心叶轮轴流式风机的设计、选型以及结构优化提供依据。     

掠形叶片轴流叶轮旋转频率噪声辐射的理论研究

分析了掠形叶片轴流叶轮的降噪机理。依据气－固相互作用的声辐射机制，推导了叶片第ｋ叶元体环形运动的声辐射理论，建立了掠形叶片轴流叶轮旋转频率噪声数学模型，并通过实验验证了理论的正确性。     

两种不同结构空调器轴流风机内流及性能分析

应用Navier-Stokes方程和RNGκ-ε湍流模型对空调器用轴流风机系统的内流特性进行三维数值模拟。针对匹配同一室外机时出现的不同叶片数目的叶轮,采用数值模拟与外部性能实验相结合的方法,对不同结构的两/三叶片风轮使用时的内部流场及气动性能进行详细分析。实验分析结果显示,两/三叶片叶轮各具特点,三叶片风轮匹配室外机时,风轮出口的轴向速度变化梯度较小,且气流扰动较小,能够有效地降低风机的相对湍流强度,改善气动噪声,实现降低噪声2.2dB（A）。而两叶片风轮用材少,质量轻,电功率消耗比三叶片风轮降低3.25%-6.06%,表明其具有良好的节能效果。     

Damages of wind turbine blade trailing edge: Forms,location, and root causes

The geometrical form and the manufacturing technique make the trailing edge of the wind turbine blade more susceptible to damage. In this study the trailing edge in a number of 81 blades of 100 kW wind turbines and 18 blades of 300 kW wind turbines of working life ranging between 6.5 × 10⁷ and 1.1 × 10⁸ cycles were completely visually scanned. The different damages were classified and allocated in their exact position relative to the blade length. Cracks in different orientations with the blade length were the frequent types of damages which found on the trailing edge. First, longitudinal cracks (LCs) that found along the blade trailing edge from the blade root to the tip were in lengths that varied from a few centimeters up to around 1.35 m. Second, transverse cracks (TCs) were found in either simple TCs which growing on one shell at the trailing edge or round TCs which growing across the two shells. TCs lengths were ranging from 20 to 50 mm. Third, edge damages were detected in the form of edge cuts or crushing. The possible root causes of the different types of cracks have been discussed.     

Experimental and numerical studies on the performance and surface streamlines on the blades of a horizontal-axis wind turbine

Investigating laminar separation over the turbine blade of a horizontal-axis wind turbine (HAWT) has been considered an important task to improve the aerodynamic performance of a wind turbine. To better understand the laminar separation phenomena, in this study, the aerodynamic forces of a SD8000 airfoil (representing the sectional blade shape) in the steady-state conditions were first predicted using an incompressible Reynolds-averaged Navier–Stokes solver with the γ–Re _θt and k–k _L–ω transition models. By comparing simulation and experimental results, the k–k _L–ω transition model was chosen to simulate the laminar separation on three-dimensional (3D) turbine blade. Experimentally, a HAWT with three blades was then tested in a close-circuit wind tunnel between the tip speed ratios (TSRs) of 2 and 7 at the wind speed of 10 m/s. In addition, through computational fluid dynamics, the turbine performance and flow characteristics on the blade as blade is rotating were investigated. It is shown that 3D simulations agreed well with the experimental results with regard to the mechanical power of the HAWT at the testing TSRs. Moreover, the separation and reattachment lines on the suction surface of the turbine blade were also observed through the skin friction line, indicating that laminar separation moved toward the trailing edge with the increasing TSR at the blade tip region.     

Optimization design of axial fan blade

A series airfoil was obtained through optimization design which aimed to promote lift–drag ratio, and the new airfoil series was used to construct a blade. The chord length and installation angle of the blade along the blade height were optimized by using orthogonal optimization. Three design options (straight blades, C-type blades and forward swept blades) are examined in this paper. Taking an axial fan as the research object, the whole 3D numerical simulation was conducted by using Ansys-CFX. Axial fans with three kinds of blades are discussed and compared under design and off-design conditions. The present results show that: under design conditions, the total pressure efficiency of the axial flow fan with the forward swept blade is the highest, and the C-type blade has slightly lower efficiency while the straight blade has the lowest efficiency. Under off-design conditions, the aerodynamic performance of the forward-swept blade and C-type blade fans are better than that of the straight-blade fans.     

Numerische Strömungssimulation an einer Niedergeschwindigkeits-Axialturbine unterschiedlichen Deckband-Abschirmungen des Laufrades

The numerical simulation of the flow through a low-speed turbine stage followed by a vane row is presented for two experimentally investigated shrouds of different weight and shape. The aerofoil-pressure distribution of the blades and vanes as well as the flow at the exit of the bladerow is compared in the experimentally and numerically obtained results. In addition to experimental data published earlier, numerical flow results are added, which had been inaccessible in the experiment. The choice of the turbulence model influences substantially the result of the numerical simulation for the flow leaving the rotor blade row. Furthermore the computational result shows the influence of the flow pattern in the labyrinth cavity on the power loss. The prediction of the static pressure decrease along the flow path through the seal across the cavities concludes this investigation.     

An investigation on the failed blades in a locomotive turbine

A failure investigation has been conducted on the turbine blades used in a locomotive turbochanger, which are made from K418 Ni-base superalloy. Fractography investigation on the troubled blade indicates that cracks initiated from the surface of the concave side close to the trailing edge and propagated towards to the leading edge. The multi-origin fatigue fracture is the dominant failure mechanism of the blade. Metallographic morphology typical of over-heat damage features, such as re-dissolution of the eutectic γ + γ′, melting of the local region of the grain boundary appears in the microstructure of the airfoil part of the failed blades. Appearance of over-heat damage structure in the serviced blades makes the strength of the blade material decrease intensely to initiate fatigue cracks and make one of the blades fracture first. Fragments from the blade fractured first would crash the other blades to make the blades break or bending deformation.     

空调离心叶轮尾流噪声的数值预估

由于现有的计算技术限制,风机气动噪声的数值预估是非常困难的。对于单个离心叶轮,已知其最主要的气动噪声源是叶片尾缘涡脱落导致的叶片表面压力脉动。基于Lee(1993)的轴流风机尾流噪声模型,提出一种可适用于离心叶轮尾流噪声数值预估方法。它包括三项主要工作:首先利用商用CFD软件Fluent对叶轮内的三维流场进行了数值模拟,并对所得气动性能进行实验验证;然后对叶片尾缘附近的速度剖面进行分析,提取出吸力面和压力面两侧的边界层厚度;最后,根据改进的噪声预估模型对叶轮的总声压级进行数值预估,在设计工况附近所得结果与实验值相比误差小于3dB。     

基于矩形流道流场分析及气动实验的轴流风机结构参数优化设计

本文通过提取导流罩的轴向长度及叶顶间隙两个设计参数,构建了矩形流道内轴流风机的流场结构及仿真模型,进行了数值模拟和实验分析。结合仿真模型分析了矩形风道下轴流风机内部和出口流场特性的变化规律,构建了风机设计参数与气动性能之间的映射关系模型。通过风机气动性能实验可得:风机出口静压、体积流量和效率与间隙因子成反比,而与长度因子成正比,对比模拟值和实验值验证了模型的正确性。基于量化映射关系模型得到风机设计参数间隙因子和长度因子的最优值分别为0.8%和12.5%,为风机设计和冰箱风道优化提供量化参考。     

Application of IR thermography as a measuring method to study heat transfer on rotating surface

This paper presents an experimental and CFD numerical study of convective heat transfer and flow field characteristics in a rotating environment. Surface temperature distribution on a rotating blade was measured by means of infrared thermography. The experimental facility, IR thermography method, and the CFD numerical model that was made according to the actual test rig geometry and operating conditions, are described in detail. For the present study, tests were carried out at relatively low fluid temperatures in several operating points, defined by rotational, Reynolds and hot-to-cool air mass flow ratio. Experimental and numerical results for the observed blade side are compared in terms of surface temperature distribution (2D) and 1D charts along the blade midspan. Temperature distributions are statistically evaluated and show very good agreement.     

一种叶片前后缘削边形状计算方法

目前主要采用依据标准图样目视判断的方法分析加工后的叶片前后缘形状,存在测量效率低、重复性差、评价结果不一致等问题。本文提出基于厚度偏差趋势判断前后缘形状的方法,利用叶片截面中弧线分割叶片边缘厚度,根据评价区域最大厚度偏差、最大厚度偏差比和厚度偏差变化率系数,自动分析叶片前后缘削边形状。该方法具有快速、准确的特性,为发动机叶片加工质量的评价提供了重要保障。     

叶片厚度变化对船用轴流涡轮性能的影响

目的 研究船用轴流涡轮叶片厚度对涡轮性能的影响,为高性能涡轮设计提供参考。方法 基于计算流体力学(CFD)仿真,模拟分析了2种叶片厚度下的叶片压力、涡轮流通特性及效率特性。结果 在相同膨胀比条件下,当叶片厚度从16.12 mm增大至16.61 mm(叶根处宽度)时,折合流量下降。当膨胀比从1.5增大到2时,加厚叶片的折合流量从0.216增长至0.238,未加厚叶片的折合流量从0.219增长至0.243。当膨胀比从2继续增大时,涡轮流量随膨胀比的变化而趋于平缓。当膨胀比约为2时,涡轮效率达到最高。采用加厚叶片时,涡轮效率最高达到0.815;当膨胀比为1.5~2.68时,涡轮效率在0.8以上。当采用未加厚叶片时,涡轮效率最高达到0.808;当膨胀比为1.6~2.38时,涡轮效率才能达到0.8以上。结论 转子叶片的加厚有利于降低能量损失,且叶片表面产生旋转涡流有助于减轻尾缘处的速度冲击,进一步降低了能量损失;但转子叶片过厚会限制流体的通量,使转子的通流面积减小,涡轮的折合流量减小;在大膨胀比条件下,加厚叶片涡轮的堵塞流量明显小于未加厚涡轮的。涡轮效率随膨胀比的增大而先增大后减小。随着叶片厚度的增大,涡轮整体效率增大,高效区范围增大。     

Surface Degradation and Cracking in Combustion Turbine Blade Cooling Passages

The depth of internal oxidation and nitridation from the surface of the 16 cooling holes in a first-stage turbine blade was measured by optical microscopy after 32,000 hours of service. Maximum depth of penetration was 15.5 mils (0.4 mm) at the trailing edge hole. An effort was made to predict hole surface metal temperatures based on these measurements using the Arrhenius relationship between time and temperature with depth of oxidation assumed to be parabolic with time. Good correlations were obtained between the finite element analysis results and the predictions. In the thickest part of the airfoil, where metal temperature is minimum, intergranular cracks up to 1.2.6 mils (0.32 mm∥ in depth were found at the surface of the cooling holes. Measurable attack was only one to two mils (0.025-0.050 mm). Based on an approximate elastic-relaxation-local inelastic stress analysis, it was calculated that inelastic local strains of over one percent occur at the points of cracking. No cracking was observed in the hotter holes, but cracking did occur in a trailing edge tip cooling hole when weld repair of the tip squealer was attempted indicating that embrittlement had occurred from the environmental attack.     

2 MW风机叶片的结构设计及静力学分析

以2 MW风力发电机叶片为研究对象,通过Matlab中的优化函数fmincon对风机叶片的关键参数(弦长、扭角、轴向和周向因子)进行优化.采用UG建模,导入ABAQUS分析软件,将叶片分为叶片根部、主梁、前缘、后缘、腹板5个部分分区域铺层后,对其施加载荷进行静力学分析,分析不同部位应力和应变规律,同时对叶根部位的复合材料层间力进行分析.结果表明:叶片根部为应力最大部位,最大变形部位为叶片端部;-45°铺层的层间应力最大,而且应力随铺设角度的不同呈现出周期性变化.通过对叶片进行静力学分析和层间力分析,能够对叶片铺层设计提供可靠的依据.     

Thermo-mechanical Fatigue Failure of a Low-Pressure Turbine Blade in a Turbofan Engine

This paper concerns a failure analysis case study of low-pressure turbine blades in an aero-engine. The operational condition of the engine was studied, and metallurgical investigations were carried out on two fractured blades. The failure in one blade originated at the leading edge, while in another it originated at the trailing edge then propagated in the forward direction. The crack propagation region showed mixed mode fractographic characteristics before the final failure. The mixed mode region was considered indicative of a thermo-mechanical fatigue propagation mode. Surface analysis of the blades indicated oxidation of variant thicknesses including oxide-filled intergranular cracks and grain boundary thickening beneath the oxide layer. It is considered more probable that the mechanism was more oxidation and fatigue dominated as opposed to creep-related.     

Study of the fracture of the last stage blade in an aircraft gas turbine

The fracture on the blade in an aircraft gas turbine has been studied to see the cause of crack initiation. The turbine blades were made of Ni-base superalloy of MAR 200Hf grade and fabricated by DS investment casting. From the visual examination of the fractured surface, the turbine blade had initially cracked by a fatigue mechanism over a period of time and then fractured by the overload at the last moment. On further examination, the crack initiated at the trailing edge of the blade, and propagated by the fatigue under the cyclic loading experienced by the blade during service. The pores and segregated area of Hf and Ti at the trailing edge of the blade, caused by DS investment casting, is found by the microstructure and EDX analysis of the blade. The crack initiated at this area and was due to the stress concentration at the pores and segregation of Hf and Ti.