Optimum Profiles of Endwall Contouring for Enhanced Net Heat Flux Reduction and Aerodynamic Performance

Successfully utilized non-axisymmetric endwalls to enhance turbine efficiencies(aerodynamic and turbine inlet temperatures)by controlling the characteristics of the secondary flow in a blade passage.This is accomplished by steady-state numerical hydrodynamics and deep knowledge of the field of flow.Because of the interaction between mainstream and purge flow contributing supplementary losses in the stage,non-axisymmetric endwalls are highly susceptible to the inception of purge flow exit compared to the flat and any advantage rapidly vanishes.The conclusions reveal that the supreme endwall pattern could yield a lowering of the gross pressure loss at the design stage and is related to the size of the top-loss location being productively lowered.This has led to diminished global thermal exchange lowered in the passage of the vane alone.The reverse flow adjacent to the suction side corner of the endwall is migrated farther from the vane surface,as the deviated pressure spread on the endwall accelerates the flow and progresses the reverse flow core still downstream.The depleted association between the tornado-like vortex and the corner vortex adjacent to the suction side corner of the endwall is the dominant mechanism of control in the contoured end wall.In this publication,we show that the non-axisymmetric endwall contouring by selective numerical shape change method at most prominent locations is advantageous in lowering the thermal load in turbines to augment the net heat flux reduction as well as the aerodynamic performance using multi-objective optimization.

Airfoil friction drag reduction based on grid-type and super-dense array plasma actuators

To improve the cruise flight performance of aircraft, two new configurations of plasma actuators(grid-type and super-dense array) were investigated to reduce the turbulent skin friction drag of a low-speed airfoil. The induced jet characteristics of the two actuators in quiescent air were diagnosed with high-speed particle image velocimetry(PIV), and their drag reduction efficiencies were examined under different operating conditions in a wind tunnel. The results showed that the grid-type plasma actuator was capable of producing a wall-normal jet array(peak magnitude: 1.07 m/s) similar to that generated in a micro-blowing technique, while the superdense array plasma actuator created a wavy wall-parallel jet(magnitude: 0.94 m/s) due to the discrete spanwise electrostatic forces. Under a comparable electrical power consumption level,the super-dense array plasma actuator array significantly outperformed the grid-type configuration,reducing the total airfoil friction drag by approximately 22% at a free-stream velocity of 20 m/s.The magnitude of drag reduction was proportional to the dimensionless jet velocity ratio(r), and a threshold r = 0.014 existed under which little impact on airfoil drag could be discerned.

Influence of Flap Parameters on the Aerodynamic Performance of a Wind-Turbine Airfoil

A numerical method has been used to analyze the flow field related to a NACA 0015 airfoil with and without a flap and assess the influence of the flap height and angle on the surface pressure coefficient,lift coefficient,and drag coefficient.The numerical results demonstrate that the flap can effectively improve the lift coefficient of the airfoil;however,at small attack angles,its influence is significantly reduced.When the angle of attack exceeds the critical stall angle and the flap height is 1.5%of the chord length,the influence of the flap becomes very evident.As the flap height increases,the starting point of the separation vortex gradually moves forward and generates a larger wake vortex.Optimal aerodynamic characteristics are obtained for 1.5%(of the chord length)flap height and a 45°flap angle;in this case,the separation vortex is effectively reduced.

TOPOLOGY AND VORTEX STRUCTURES OF A CURVING TURBINE CASCADE WITH TIP CLEARANCE (Ⅰ)- EXPERIMENTAL MODEL AND TOPOLOGICAL FLOW PATTERNS ON BOTH ENDWALLS AND BLADE SURFACES

By means of ink trace visualization of the flows in conventional straight, positively curved and negatively curved cascades with tip clearance, and measurement of the aerodynamic parameters in the transverse section, and by appling topology theory, the structures on both endwalls and blade surfaces were analyzed. Compared with conventional straight cascade, blade positive curving eliminates the separation line of the upper passage vortex and leads the secondary vortex to change from close separation to open separation, while blade negative curving effects merely the positions of singular points and the intensities and scales of vortex.

Optimal Design of Non-axisymmetric Endwall with Variable-fidelity CFD Model

Non-axisymmetric endwall is numerically investigated to suppress the secondary endwall flow in a HP turbine suction surface.The endwall contour is represented by a non-uniform rational B-spline surface.Two solution spaces are designed by the rule of hypercube sampling through variation of nodal radial extension.Final most effective endwall contour is obtained through screening all available samples with surrogate-based model.Results show that non axisymmetric endwall reduces the turbulence kinetic energy of the passage vortex by 5.5%and the total pressure loss 1.6%.Local heat transfer coefficient is lowered on the afore passage endwall surface with a certain increment on the aft passage endwall.Overall averaged heat transfer coefficient is reduced.

Influence of Endwall Contouring on the Secondary Flow in Turbine Nozzle Guide Vane

Numerical simulations are carried out to investigate the effect of the endwall contouring on the secondary flow in turbine nozzle guide vane.The three contoured cascades with the same contouring profile and the different positions where the contoured profile locates at are researched.The results show that the contouring configuration can reduce the aerodynamic losses of the cascade.The flat side takes advantage of a stronger decrease of the losses,compared to the contoured side.The contouring configuration can also inhibit the secondary flow.The contoured cascade in which the contouring profile starts upstream of the airfoil,ends at the middle of the airfoil has the best effect of improving secondary flow.

Numerical Study on Low-Reynolds Compressible Flows around Mars Helicopter Rotor Blade Airfoil

High-speed rotor rotation under the low-density condition creates a special low-Reynolds compressible flow around the rotor blade airfoil where the compressibility effect on the laminar separated shear layer occurs. However, the compressibility effect and shock wave generation associated with the increase in the Mach number (M) and the trend change due to their interference have not been clarified. The purpose is to clear the compressibility effect and its impact of shock wave generation on the flow field and aerodynamics. Therefore, we perform a two-dimensional unsteady calculation by Computational fluid dynamics (CFD) analysis using the CLF5605 airfoil used in the Mars helicopter Ingenuity, which succeeded in its first flight on Mars. The calculation conditions are set to the Reynolds number (Re) at 75% rotor span in hovering (Re = 15,400), and the Mach number was varied from incompressible (M = 0.2) to transonic (M = 1.2). The compressible fluid dynamics solver FaSTAR developed by the Japan aerospace exploration agency (JAXA) is used, and calculations are performed under multiple conditions in which the Mach number and angle of attack (α) are swept. The results show that a flow field is similar to that in the Earth’s atmosphere above M = 1.0, such as bow shock at the leading edge, whereas multiple λ-type shock waves are observed over the separated shear layer above α = 3° at M = 0.80. However, no significant difference is found in the Cp distribution around the airfoil between M = 0.6 and M = 0.8. From the results, it is found that multiple λ-type shock waves have no significant effect on the airfoil surface pressure distribution, the separated shear layer effect is dominant in the surface pressure change and aerodynamic characteristics.

Fourier neural operator with boundary conditions for efficient prediction of steady airfoil flows

An efficient data-driven approach for predicting steady airfoil flows is proposed based on the Fourier neural operator(FNO),which is a new framework of neural networks.Theoretical reasons and experimental results are provided to support the necessity and effectiveness of the improvements made to the FNO,which involve using an additional branch neural operator to approximate the contribution of boundary conditions to steady solutions.The proposed approach runs several orders of magnitude faster than the traditional numerical methods.The predictions for flows around airfoils and ellipses demonstrate the superior accuracy and impressive speed of this novel approach.Furthermore,the property of zero-shot super-resolution enables the proposed approach to overcome the limitations of predicting airfoil flows with Cartesian grids,thereby improving the accuracy in the near-wall region.There is no doubt that the unprecedented speed and accuracy in forecasting steady airfoil flows have massive benefits for airfoil design and optimization.

Design and Structure Optimization of Plenum Chamber with Airfoil Baffle to Improve Its Outlet Velocity Uniformity in Heat Setting Machines

The plenum chamber of a heat setting machine is a key structure for distributing hot air to different air channels.Its outlet velocity uniformity directly determines the heating uniformity of textiles,significantly affecting the heat setting performance.In a traditional heat setting machine,the outlet airflow maldistribution of the plenum chamber still exists.In this study,a novel plenum chamber with an airfoil baffle was established to improve the uniformity of the velocity distribution at the outlet in a heat setting machine.The structural influence of the plenum chamber on the velocity distribution was investigated using a computational fluid dynamics program.It was found that a chamber with a smaller outlet partition thickness had a better outlet velocity uniformity.The structural optimization of the plenum chamber was conducted using the particle swarm optimization algorithm.The outlet partition thickness,the transverse distance and the longitudinal distance of the optimized plenum chamber were 20,686.2 and 274.6 mm,respectively.Experiments were carried out.The experimental and simulated results showed that the optimized plenum chamber with an airfoil baffle could improve the outlet velocity uniformity.The air outlet velocity uniformity index of the optimized plenum chamber with an airfoil baffle was 4.75%higher than that of the plenum chamber without an airfoil baffle and 5.98%higher than that of the conventional chamber with a square baffle in a commercial heat setting machine.

Optimized Design of H-Type Vertical Axis Wind Airfoil at Multiple Angles of Attack

Numerical simulations are conducted to improve the energy acquisition efficiency of H-type vertical axis wind turbines through the optimization of the related blade airfoil aerodynamic performance.The Bézier curve is initi-ally used tofit the curve profile of a NACA2412 airfoil,and the moving asymptote algorithm is then exploited to optimize the design of the considered H-type vertical-axis wind-turbine blade airfoil for a certain attack angle.The results show that the maximum lift coefficient of the optimized airfoil is 8.33%higher than that of the original airfoil.The maximum lift-to-drag ratio of the optimized airfoil exceeds the maximum lift-to-drag ratio of the ori-ginal airfoil by 11.22%.Moreover,the power coefficient is increased by 12.19%and the torque coefficient of the wind turbine is significantly improved.

融合多源数据挖掘信息的非轴对称端壁/叶身联合成型设计空间知识挖掘

为厘清联合成型设计空间各造型方法对涡轮叶栅性能提升的贡献,将基于总变差分析的全局敏感性分析方法与平行坐标系及直方图、散点图等可视化技术相结合,提出了将多源数据挖掘信息进行融合的设计空间知识挖掘框架,并利用该框架对某小展弦比叶栅端壁/叶身联合成型设计空间进行知识挖掘。结果表明:叶栅气动损失增减对基元型线微调十分敏感;非轴对称端壁所带来的损失减少量与型线微调接近,但设计空间内不同非轴对称端壁样本性能波动较小,导致其重要性被全局敏感性分析方法低估;虽然单独采用弯叶片难以整体降低小展弦比叶栅损失,但将弯、型线微调和非轴对称端壁造型相结合可获得“1+1+1>3”的性能增益;在端壁/叶身联合成型设计空间内,将基元型线朝着后加载方向微调,并采用喉部附近下凹较深的非轴对称端壁造型及反弯叶片设计,可获得气动损失较小的叶栅设计。研究结果明晰了端壁/叶身联合成型设计空间优化解特征,可为类似小展弦比叶栅设计优化提供借鉴。

改变导叶翼型对水泵水轮机“S”特性的影响

针对水泵水轮机“S”特性区域的不稳定性问题,提出使用改型活动导叶翼型进行性能提升.以某水泵水轮机模型为研究对象,采用SST k-ω湍流模型对水泵水轮机全流道进行三维数值计算,通过对活动导叶翼型的改型设计,得出流量-转速模拟曲线,分析水泵水轮机组“S”特性改善情况.将计算与试验结果进行对比,并对改型活动导叶翼型前后机组的无叶区进行压力脉动分析.结果表明:在保证整体效率依然保持在92%附近的前提下,新的活动导叶翼型对机组的“S”特性依旧具有改善效果;无叶区压力脉动主要是受到活动导叶叶栅区域的分流在此重新聚集影响,并且与转轮叶片的动静相互扰动引起的;改型后的活动导叶降低了无叶区的压力脉动幅值,提升了水泵水轮机运行中的并网稳定性.

翼型叶片安装方式对粉煤灰气力输送的影响

针对当前螺旋流气力输送中有关叶片安装方式的研究,分析了典型NACA系列翼型截面叶片应用于起旋装置时的流场。通过对观测面轴向流速与切向流速的仿真,计算叶片不同安装方式与安装角度时螺旋流场的旋流强度,确定了前缘迎风的安装方式比尾缘迎风起旋效果更强;安装方式固定时,旋流强度随安装角度的增大而减小。

风电NACA63418翼型参数化建模及优化

风力发电机的风轮气动效率与优良翼型的气动性能密切相关。以风力机传统翼型为研究对象,结合翼型参数化建模及自适应遗传算法,寻优搜索得到高性能优化翼型。比较了CST法和改进的Hicks-Henne型函数法对于NACA63418传统翼型的拟合精度,进而选用Hicks-Henne型函数法对NACA63418翼型进行参数化建模。通过自适应遗传算法和XFOIL软件耦合实现翼型气动特性的自动计算,提高翼形的设计效率,为翼型的理论设计拓宽了思路。

前缘圆柱对风力机翼型气动性能及冲蚀磨损影响研究

为研究风沙环境下流动控制方式对于NACA 0012翼型气动性能和冲蚀磨损的影响,通过在风力机翼型前缘布置微小圆柱来控制气流流动,采用离散项模型和SST k-ω湍流模型对控制翼型进行数值计算。结果表明:攻角较小时,微小圆柱处于X=0.04、Y=-0.03位置时控制效果最佳,可抑制流动分离,相比原翼型升阻比提高149.72%;微小圆柱处于X=0.02、Y=-0.02位置时翼型冲蚀磨损的减小量最大,相比原翼型减小97.66%;微小圆柱处于最优区域时翼型升阻比提高的同时冲蚀磨损量也会减小。

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。

S型翼缝与尾缘襟翼联合控制风力机翼型气动性能的研究

降低叶片气动载荷对于延长风力机叶片寿命极为重要,尾缘襟翼是降低叶片气动载荷的一种有效手段,然而其在大攻角下对翼型的气动特性控制效果减弱。通过在50%叶片弦长处添加S型翼缝,采用数值模拟方法研究S型翼缝与尾缘襟翼联合调节风力机叶片气动特性的作用。利用剪切应力输运(shear stress transport,SST)湍流模型,计算模拟了S809翼型在雷诺数106下,S型翼缝与尾缘襟翼联合控制对翼型气动特性的影响,并分析了S型翼缝与尾缘襟翼的协同控制机理。结果表明,尾缘襟翼的偏转可显著改变翼缝槽内的气体流量,并有效调节叶片中部的压差,这种联合控制策略可在大攻角下大幅改善翼型的失速现象,从而显著增强尾缘襟翼对升力系数的调控能力。

采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化

为了提升高负荷涡轮级的气动效率,发展了基于样条曲面的非轴对称端壁造型方法。以该参数化造型方法为基础,结合高效智能优化算法和经过校核的数值仿真方法,建立了涡轮非轴对称端壁设计优化平台,并以某小展弦比高压涡轮级为研究对象,以效率为优化目标,以流量为约束条件,在级环境和发动机工况下开展了非轴对称端壁优化设计。结果表明:优化设计后的涡轮动叶相对于参考设计,涡轮级的总总效率提升0.26%;非轴对称端壁造型改变了动叶下端壁附近的压力分布,动叶吸力面侧压力系数相对于参考设计显著提升,这降低了动叶叶片通道内的横向压力梯度,抑制了通道中的二次流动;非轴对称端壁造型改变了叶片通道中的涡系结构,相对于参考设计,非轴对称端壁造型使得马蹄涡压力面分支在叶片通道内部沿着叶片压力面迁移,在靠近通道出口的位置才汇入通道涡,这削弱了通道涡的强度,进而降低了气动损失,提高了涡轮级效率。

燃烧室百叶与双排孔冷气对透平端壁冷却性能影响研究

针对燃烧室与透平冷气掺混导致实际二次流发展及端壁冷却性能偏离设计值的问题,综合考虑燃烧室百叶冷气尾迹与双排孔射流,数值研究了多源冷气射流在燃烧室与透平交界区的掺混机制,分析了其对透平静叶端壁气膜冷却与流动特性的影响规律。研究结果表明:空腔涡卷吸大部分百叶冷气,并跨越双排孔冷气向下游发展,马蹄涡卷吸限制大部分双排孔冷气,并向空腔涡外侧发展;当双排孔冷气吹风比M_h=0.5,1.0较小时,马蹄涡导致冷气形成楔形高冷效区域,空腔涡的附着侧和分离侧分别产生了高、低冷效区,随着百叶冷气吹风比M_l的增加,空腔涡强度显著降低,导致位于楔形中心的分离侧冷却效率有所提升;当双排孔冷气吹风比M_h为1.5时,双排孔冷气部分跨越马蹄涡,静叶端壁可实现完全冷气覆盖,此时百叶冷气吹风比M_l从0.5增加到1.5,静叶端壁平均冷却效率可从0.4提升到0.63。该研究为考虑燃烧室与透平交界区实际流动掺混情况的静叶端壁冷却结构与布局设计提供理论基础。

NACA0021和NACA4822翼型肋通道中环境空气流动传热特性的实验研究

针对超燃冲压发动机在更高Mach数飞行时,主动再生冷却技术面临换热能力不足的瓶颈问题,拟利用翼型肋加强再生冷却通道的传热性能.为了从原理上验证翼型肋通道的强化传热效果,搭建了环境空气在NACA0021对称翼型肋和NACA4822非对称翼型肋通道(横截面尺寸50 mm×50 mm)中的流动传热实验测试平台,基于稳态液晶技术得到受热表面的Nusselt数.通过实验研究发现:NACA0021对称翼型肋通道和NACA4822非对称翼型肋通道的传热强度分别被提升了0.17%~17.1%和18.4%~52.1%,50 m^(3)/h流量下的PEC(performance evaluation criteri-on)分别为1.04和1.24;大流量条件下,NACA4822非对称翼型肋通道可强化中间受热面的传热性能;翼型肋通道中的流动压降也会相应增大,其中NACA4822翼型肋通道中的压降最大,翼型肋的非对称性使得流动湍流强度不断积累造成下游压降存在明显升高.该研究将有助于进一步开展翼型肋通道内超临界流体的流动传热特性研究,拓宽超燃冲压发动机主动再生冷却技术的应用温区.