采用冷气射流调节对转涡轮高压部件流量的数值研究

针对先进发动机对涡轮变工况流量调节的需求,以某对转涡轮高压部件为研究对象,采用源项法模拟冷气射流,对导叶压力面、吸力面射流孔位置、射流角及射流流量对涡轮流量调节效果的影响进行了数值研究.结果表明:射流轨迹通过堵塞流道能实现减小涡轮进口流量的需求;从流量调节效果而言,不存在最佳压力面射流位置,而最佳吸力面射流位置位于喉道...     

轮缘密封气流影响下的涡轮静叶通道流动特性研究

为探讨轮缘密封气流对高压涡轮静叶通道内流动特性的影响,采用SST湍流模型求解三维非定常雷诺方程,分析无封严腔、无封严气流以及4种封严流量下涡轮静叶通道内压力波动和气流变化。研究结果表明：封严腔出口受上游静叶压力场影响较大,燃气入侵发生在静叶尾缘附近压力面和吸力面两侧气流交汇形成的高压区;封严出流发生在静叶通道中间位置受吸力面侧扩压区影响的低压区;封严出流与主流掺混形成的新涡量结构卷吸了部分附面层流体,削弱了二次流结构的强度,同时对主流通道形成堵塞效应,推动了轮毂二次流向吸力面靠近同时径向位置的抬升;盘泵效应导致的封严出流与主流的掺混增强了非定常效应,封严流量的增大能够抑制通道内非定常效应。     

双流道泵内非定常流动数值模拟及粒子图像测速测量

为探讨双流道泵内部的非定常流动机理,采用Fluent软件,基于滑移网格技术、 湍流模型计算了一双流道泵在不同工况下的内部流动,并将计算结果与粒子图像测速仪(Particle image velocimeter, PIV)实测结果进行比较。结果表明：计算所得双流道泵内部流场符合叶轮机械内部流动的一般规律,且与PIV实测结果总体变化趋势一致;由于双流道泵结构特殊,其进口处的流动状态与普通叶轮相差较大,出口处的流动状态与普通叶轮类似;叶轮进口处,流体基本沿流道吸力面流动,流道工作面上的相对速度很小,存在严重的脱流和旋涡;叶轮出口处,压力面和吸力面的速度趋于相等,射流—尾迹现象并不明显;由于叶轮—蜗壳动静干涉,两个叶轮流道内的静压分布有所不同;同一流道内,静压随着半径的增加而逐步增大,压力面侧静压大于吸力面侧;蜗壳流道内静压随半径增大,最大静压值在隔舌处。此项研究不仅加深了人们对双流道泵内非定常流动图画的理解,从而进一步完善双流道泵设计方法,同时也可为其他类型泵的内流研究提供借鉴。     

调速型液力偶合器制动工况流场分析

基于三维多相流动理论和计算流体动力学(CFD),对调速型液力偶合器制动工况下的非稳态两相流动进行数值模拟。结果表明:泵轮流道的压力分布较规律,沿径向成比例逐渐增大,而涡轮流道的内部流动则较复杂;涡轮吸力面出现了小范围的不规则流动现象;中间轴面的速度分布较复杂,涡轮速度小于泵轮速度;Interface中部的低速区出现降低偶合器效率的二次流。对调速型液力偶合器制动工况进行流场分析,揭示其泵轮和涡轮的流场流动规律和特性,有助于指导液力偶合器的设计,提高偶合器的性能。     

合成射流对钝尾缘翼型气动特性的影响

研究吸力面存在合成射流的情况下,钝尾缘翼型TR-4000-2000流场结构的变化及其升阻力系数等气动特性参数的变化趋势。在相同射流入口速度条件下,采用计算流体力学软件Fluent对相同来流速度不同攻角情况下翼型流场进行非定常数值模拟计算,分析射流前后翼型升阻力系数变化及翼型表面压力的波动状况;在此基础上,对不同射流频率和不同射流速度情况下翼型流场进行模拟计算,寻求最佳射流参数。结果表明,由于射流及尾缘涡的相互作用导致翼型的升阻力特性不断变化,钝尾缘翼型吸力面合成射流有明显的增升减阻效果,在15°攻角时尤为明显,升力系数提高约40%,阻力系数减小约25%。在量纲一射流速度和量纲一射流频率均为1时,射流对翼型的增升减阻效果最佳。     

CFD investigation on the flatback airfoil effect of 10 MW wind turbine blade

The flatback airfoil effect on the inboard region of a large wind turbine blade was investigated by numerical analysis. Complicated flow phenomena in wind turbine blade with flatback and non-flatback airfoil were captured by Reynolds-averaged Navier–Stokes flow simulation with shear stress transport turbulence model. Although both airfoil blades were designed using blade element momentum theory to produce identical shaft power, results of three-dimensional computational fluid dynamics (CFD) flow analysis indicated that at a specific location of the root area, the flatback airfoil improved the inboard force by approximately 6 % compared with the non-flatback airfoil. We were also able to confirm that by using the flatback airfoil, the overall shaft power throughout the blade increased by 1 %, thereby restraining the bending moment exerted by the thrust force on the hub by 0.5 %. Moreover, numerical analysis results indicated that the flatback airfoil blade reduced the size of the secondary vortex around the blade root area and its progress in the secondary direction in comparison with the non-flatback airfoil blade. The shape of the flatback airfoil on the trailing edge weakened the adverse pressure gradient migrating from the lower to the upper surface. Regardless of the flatback airfoils, the tip vortex core of the outboard region formed on the suction surface leading edge and strongly rolled up by the pressure surface boundary layers due to the large pressure difference between the suction and pressure surfaces in the blade tip region. This remarkable strong tip vortex developed downstream and raked up the boundary layer of the blade trailing edge with low energy.     

定向喷嘴布置对PDC钻头井底流场影响研究

定向喷嘴布置的方式对PDC钻头的井底流场将有很大的影响,尤其是能改变PDC钻头的水力性能,因而研究定向喷嘴布置具有重要的意义.本文分析了喷嘴的不同布置方法,并通过数值方法模拟其对PDC钻头井底流场的影响.结果表明:在不完全对称布置方案的冲击区,在射流刚开始从喷嘴处流出去,但还未接触井底,各喷嘴射流处于衰减地带之内,这样的话将对钻头的清洗和携带岩屑离开井底非常有效果;在漩涡区,喷射角大、距钻头中心远的喷嘴射流则对清洗和携带井壁附近的岩屑起主要作用,喷射角小、距钻头中心近的喷嘴射流则对清洗和携带井底中心的岩屑起主要作用;在刀翼上的附面层由于周围喷嘴的影响,刀翼切削面低速区明显减少,剪应力增大,更好地预防、清除PDC钻头的泥包.最终达到提高机械钻速的效果.     

旋流泵内盐析两相流场的计算及试验研究

为研究流体机械内部伴有盐析的液固两相流动情况,自行设计了旋流式模型泵,采用双流体模型计算了该泵在最优工况下的氯化钠盐析两相流场,并采用先进的激光相位多普勒粒子测速仪测量了泵无叶腔及叶轮内部盐析两相流的三维速度场。将试验结果与计算结果进行对比,验证了计算模型的适用性,并给出了误差分析。通过对试验测得的周向、轴向、径向速度及其对应的脉动速度分布曲线讨论,初步揭示了该型泵内盐析两相流动特征。在整个流道内,盐析晶体颗粒大部分集中于无叶腔,且分布较均匀;进入叶轮后向叶片工作面靠拢;颗粒浓度最低处是在叶轮进口叶片背面靠近叶轮后盖板附近;液固两相在叶轮与无叶腔中的周向速度分布差异明显;两相间速度及脉动速度有滑移,但差异总体上并不显著。     

不同温度气体喷射特性的PIV试验研究

研究气体的喷射特性,用于指导发动机燃油供给系统的设计和燃烧室有效组织燃烧。基于粒子图像测速技术(PIV),对不同温度、不同压差下气体喷射的特性进行了对比研究。通过试验分析和图像处理等手段对射流流场及涡结构、气体射流边界扩展、喷嘴轴向流速衰减规律、断面流速分布等进行了总结。试验表明:射流边界呈线性扩展,可用锥角大小来表征其特性,锥角随压差的减小而增大,且增幅明显,温度对其也有一定影响。喷嘴射流的轴向速度与射流距离成反比,而速度的影响面积随射流距离的增大而增大,温度的增大使得相同压差下的轴向速度相应增大,断面流速的分布存在很大的相似性。     

离心泵叶轮内部粘油流动激光测速计测量

利用二维激光测速计系统准确地测量了离心泵输送粘度为４８ｍｍ２／ｓ粘油时最优和小流量工况叶轮内部流动。试验表明,叶片吸力面有很宽的尾流,压力面不存在射流,叶轮内部流动属主流／尾流模型。尾流位于吸力面／前盖板、吸力面／后盖板拐角处,并覆盖整个吸力面。由最优工况变到小流量工况,尾流有扩大趋势。     

Proportional feedback control of laminar flow over a hemisphere

In the present study, we perform a proportional feedback control of laminar flow over a hemisphere at Re = 300 to reduce its lift fluctuations by attenuating the strength of the vortex shedding. As a control input, blowing/suction is distributed on the surface of hemisphere before the separation, and its strength is linearly proportional to the transverse velocity at a sensing location in the centerline of the wake. The sensing location is determined based on a correlation function between the lift force and the time derivative of sensing velocity. The optimal proportional gains for the proportional control are obtained for the sensing locations considered. The present control successfully attenuates the velocity fluctuations at the sensing location and three dimensional vortical structures in the wake, resulting in the reduction of lift fluctuations of hemisphere.

     

涡轮叶栅通道中的流动显示

在大尺寸低速叶栅传热风洞中对一种高压涡轮导向叶栅的流场进行了流动显示实验研究。分别采用线簇和小球浮动法对五个雷诺数下的叶栅端壁区三维流场、叶片表面和端壁表面的流动进行了显示。实验结果表明 :涡轮叶栅中有强烈的二次流动 ,并存在复杂的涡系 ;三维流动区约占叶栅通道的 40 % ;雷诺数的增大将增强端壁区的三维流动。流场显示图片说明 :叶片吸力面靠近端壁有角涡形成与发展 ,并存在一个三角形区域 ;流场显示的通道涡大小与流场测量结果吻合。本文的实验结果可用于分析端壁表面和叶片表面换热特性的形成机理     

非设计工况下带分流叶片半开式离心叶轮内部流动特性数值研究（英文）

In order to investigate the complex flow characteristics inside an unshrouded centrifugal impeller with splitter blades at off-design conditions, and analyze its influence on pump operation stability, a numerical simulation study was carried on using the curvature-corrected SST-CC turbulence model; the head and efficiency accorded with experimental results. The pressure fluctuation, unsteady radial force and velocity were analyzed quantitatively and the numerical results indicate this: the peak to peak value of pressure fluctuation in the impeller channel gradually increases in the flow direction and at 0.49 Qn, the slope of peak to peak value to normalized impeller channel behind the splitter blade is 8.57 times greater than that before the splitter blade. The greater the flow rate deviates from the design condition, the larger the peak to peak value of the pressure fluctuation and radial force; in particular at 0.27 Qn, the maximum radial force is 194.29% greater than that of the design condition. When the operating flow rate is smaller than0.83 Qn, the stall occurs and the stall vortex could block the impeller discharge; as the flow rate decreases further, the pressure amplitude at rotational frequency gradually increases in the impeller channel and the prevailing frequency changes from the blade passage frequency(BPF) to the rotating stall frequency in the diffuser. The tip leakage vortex(TLV) is generated in the tip region and rotated move downstream in the impeller flow channel, and the backflows appear on the blade suction side and in the tip and the tongue regions; the smaller the flow rate, the more serious the TLV and backflow phenomenon. The rotating stall causes uneven flow in the impeller channel, increasing the pressure fluctuation and the radial force, and resulting in an imbalance of the impeller rotation.     

Computational investigation on secondary flows in a linear turbine cascade with tapered dual fence

The focus of the present work is to minimize the secondary flow losses inside a linear turbine cascade by means of a novel design of streamwise dual fence. The leading edge and trailing edge of the fences have been modified so as to reduce the total pressure loss coefficient in the passage. The study has been carried out computationally based on RANS simulations with SST turbulence model. Numerous simulations have been undertaken with single fence and dual fence models and compared with the base case model. The dual fence model with tapered trailing edge exhibits significant loss reduction compared to the base case. A suitable fence height ratio (FHR) has been identified for the dual fence model. The FHR = 2 configuration reduces the secondary flow kinetic energy by 78 % within the blade passage and it reduces the exit angle deviation significantly throughout the span. Detailed flow field analysis has been carried out to understand the physical mechanism behind the loss reduction with dual fence models. It is observed that fence-1 breaks the pressure side leg of the horse shoe vortex at the beginning of their formation itself. The radial penetration of the suction side leg of the horse shoe vortex is restrained by fence-2. These combined effects prevent the formation and mixing of two prominent loss core regions thereby avoiding the accumulation of low energy fluid near the suction side of blade.

     

尾缘对开缝喷气对栅后二次流发展的影响

采用数值模拟手段研究了涡轮叶片尾缘对开缝喷气栅后二次流的影响，给出了在设计工况下有、无喷气时栅后二次流影响。结果表明，喷气对栅后涡的形成和发展影响不大，而使主流区径向分量较大的区域产生漂移，并使该区域的二次流结构发生变化。     

Measurement of developing turbulent flow in a U-bend of circular cross-section

Hot-wire measurements of the full mapping of the velocity and Reynolds stress components are reported for developing turbulent flow in a strongly curved 180 deg pipe and its tangents. A slanted wire is rotated into 6 orientations and the voltage outputs from wires are combined to obtain the mean velocity and Reynolds stress components. The strength of secondary flow reaches up to the 28% of bulk mean velocity. The strong counter-rotating vortex pair induced by the transverse pressure gradient and centrifugal force imbalance grows up to Θ = 67.5° into the bend. But the vortex pair breaks down into two cell pattern after Θ=90° Core vortex formation and reversal of secondary flow direction along the bend symmetry plane is cleanly found in the secondary vector plot. At Θ=67.5° and Θ = 90° into bend a large “trough” develops in the longitudinal velocity toward the inside of the bend due to the breakdown of secondary flow. In the bend, the mean longitudinal velocity component changes little after Θ=90°, but secondary flow never achieves fully-developed state. Similar behaviors are observed in the radial and circumferential stresses.     

Numerical study of blowing and suction slot geometry optimization on NACA 0012 airfoil

The effects of jet width on blowing and suction flow control were evaluated for a NACA 0012 airfoil. RANS equations were employed in conjunction with a Menter’s shear stress turbulent model. Tangential and perpendicular blowing at the trailing edge and perpendicular suction at the leading edge were applied on the airfoil upper surface. The jet widths were varied from 1.5% to 4% of the chord length, and the jet velocity was 0.3 and 0.5 of the free-stream velocity. Results of this study demonstrated that when the blowing jet width increases, the lift-to-drag ratio rises continuously in tangential blowing and decreases quasi-linearly in perpendicular blowing. The jet widths of 3.5% and 4% of the chord length are the most effective amounts for tangential blowing, and smaller jet widths are more effective for perpendicular blowing. The lift-to-drag ratio improves when the suction jet width increases and reaches its maximum value at 2.5% of the chord length.     

Effect of convex wall curvature on three-dimensional behavior of film cooling jet

The flow characteristics of film coolant issuing into turbulent boundary layer developing on a convex surface have been investigated by means of flow visualization and three-dimensional velocity measurement. The Schlieren optical system with a spark light source was adopted to visualize the jet trajectory injected at 35° and 90° inclination angles. A five-hole directional pressure probe was used to measure three-dimensional mean velocity components at the injection angle of 35°. Flow visualization shows that at the 90° injection, the jet flow is greatly changed near the jet exit due to strong interaction with the crossflow. On the other hand, the balance between radial pressure gradient and centrifugal force plays an important role to govern the jet flow at the 35° injection. The velocity measurement shows that at a velocity ratio of 0.5, the curvature stabilizes downstream flow, which results in weakening of the bound vortex structure. However, the injectant flow is separated from the convex wall gradually, and the bound vortex maintains its structure far downstream at a velocity ratio of 1.98 with two pairs of counter rotating vortices.     

高压涡轮动叶吸力面气膜冷却特性研究

为了研究某航空发动机高压涡轮动叶吸力面的气膜冷却特性,通过数值模拟的方法,采用SST k-ω湍流模型,分析了高压涡轮动叶在静止和旋转条件下,吸力面气膜冷却效率的影响规律。结果表明:在静止条件下,相同主流湍流度时吹风比对吸力面气膜冷却效率影响显著,冷却效率随着吹风比的增大而减小;在小吹风比下,气膜冷却效率随着主流湍流度的增大而减小;在大吹风比下,气膜冷却效率随着主流湍流度的增大而增大。在相同湍流度和转速下,随着吹风比的增大,气膜向高半径偏转程度减小;在相同湍流度和吹风比下,随着转速的增大,气膜沿流向上的气膜覆盖面积减弱。优化结构的扇形气膜孔对叶片吸力面具有更好的冷却效果。     

Fluctuant pressure coefficient of the wake behind a bluff body in mist flow

Fluctuant pressure coefficient is presented as an index of vortex energy of the wake behind a bluff body in mist flow. Calculation for vortex energy is obtained from inter-phase force analysis, based on Basset-Boussinesq-Oseen equation and conservation of mechanical energy. Vortex energy is weakened by liquid disturbance, the relationship between the fluctuant pressure coefficient and liquid velocity is set up on theory analysis. An existence criterion for vortex streets is proposed using the relationship. A new algorithm for prediction of liquid velocity is put forward and compared with the method in Higham's patent. The predicted results fit the experimental results well.