汽轮机末级静叶水滴沉积规律与缝隙去湿研究

采用Fluent软件对某600 MW汽轮机末级静叶栅中的水滴三维运动与沉积规律进行了数值计算,确定了水滴在静叶轴向和径向的沉积位置;实验研究了空心叶栅缝隙抽吸的去湿性能。结果表明:静叶内弧上的沉积水量占叶栅进口总水量的12.2%,背弧的沉积水量占1.6%;静叶内弧上的缝隙抽吸水量大于背弧上的抽吸水量,缝隙位置越靠近静叶出口边,抽吸水量也越大;随着缝隙宽度的增大,缝隙抽吸水量先降低后增大,在宽度为3.0 mm左右时达到较低值;缝隙抽吸水量随抽吸压差的增大而增大,随着主气流速度的增大而很快减小。     

空心静叶缝隙抽吸对蒸汽流场影响的数值研究

在缝隙抽吸条件下,采用Fluent软件对某600MW汽轮机末级空心静叶栅内的蒸汽流场进行了三维数值模拟,讨论了缝隙位置与结构参数对主蒸汽流场的影响。结果表明:随着缝隙位置从叶片前缘向叶片尾缘的移动,汽流总压损失系数逐渐减小。缝隙抽吸使叶栅进口马赫数有所升高,且内弧上的缝隙抽吸对马赫数的影响要大于背弧上的影响;当缝隙角度α=45°时,缝隙抽吸对叶栅进口马赫数的影响较大;缝隙宽度的增大使叶栅进口马赫数升高的幅度也越大。缝隙抽吸对叶片表面压力分布总体影响不大,仅在缝隙附近的汽流静压有较大的降低;随着缝隙宽度的增加,缝隙处的汽流静压降低越大。另外,缝隙抽吸使叶片表面的汽流边界层有所减薄。     

缝隙位置对空心静叶去水性能影响的试验研究

在湿空气平面叶栅缝隙抽吸试验装置上,对汽轮机空心静叶抽吸缝隙的去水性能进行了试验研究。试验条件为:叶栅进口空气湿度为7.94%,水滴直径在1.5～150μm之间,叶栅出口气流速度为170m/s,缝隙宽度为1.0mm,缝隙角度为45°,缝隙位置分别位于静叶的内弧和背弧。试验结果表明:随着缝隙相对位置的增大,缝隙抽吸水量增大;在相同的抽吸压差下,静叶内弧上单位长度缝隙的抽吸水量大于背弧缝隙的抽吸水量;靠近静叶内弧出口边的抽吸缝隙的去水性能最好;另外,随着抽吸压差的增大,缝隙抽吸水量也增大。     

汽轮机抽汽缝宽度对邻近透平级流场的影响

用数值模拟的方法对汽轮机抽汽口前透平级、抽汽口和抽汽口后透平级的流场进行了研究,介绍了流场模拟的数学模型及其解法.描述了不同抽汽缝宽度时抽汽缝内和抽汽口透平级的流场结构.指出：抽汽使得抽汽缝内形成了一个惯性涡区,改变抽汽缝宽度将明显改变抽汽量和抽气口透平级内沿叶高的压力和速度分布;在抽汽量不变时,增大抽汽缝宽度,会使惯性涡区的尺寸加大而涡强度减弱;在抽汽端压差不变时,增大抽汽缝宽度将使抽汽口前透平级的轴向推力和扭矩增大、并降低抽汽口前后透平级的轮周效率,同时降低了整个抽汽道内的流动阻力.图10表2参6     

汽轮机空心静叶开缝抽吸除湿的数值模拟

应用两相均质混合模型和湿蒸汽平衡相变模型,对具有抽吸缝隙的某汽轮机末级叶栅流场进行了全三维定常的数值计算.计算结果表明:同一位置的缝隙,增大缝隙宽度和减少抽吸压比,将会加大缝隙抽吸量;单个方案下,结构相同的缝隙,压力面七的缝隙抽吸量一般要比吸力面上的缝隙抽吸量要大.不同方案对比发现;从气动效率及对叶栅流场的影响上,方案a优于方案b;从去水效率来说,方案b优于方案a.     

建筑一体化太阳能烟囱的通风性能研究

针对广州地区的二层别墅,在其南外墙和南向屋顶设置竖直和沿屋顶倾斜的串联太阳能烟囱,并对其通风性能进行了研究。就烟囱的总长和宽度、二层入口倾斜角度及倾斜段与竖直段长度比例等几何因素对其通风性能的影响进行了模拟计算。计算显示,随着烟囱长度的增加其通风性能随之增强;随着太阳能烟囱宽度的增加,烟囱流量先增大后减小,存在一个通风的最优长宽比,约为12:1;二层入口向下倾斜时,随着角度的增大,烟囱流量先增大后减小,最优倾角为4°;总长固定时,倾斜段与竖直段长度比例同样影响烟囱流量,按照建筑规范,建筑层高取规范最大值时烟囱流量最大。     

引气对跨声速压气机稳定性的影响

以NASA Rotor 37为研究对象,采用数值模拟方法开展了叶顶引气对转子稳定性的影响研究。结果表明:叶顶引气可以提高转子的稳定性,引气的扩稳机理在于引气口的抽吸作用,这种作用使得转子叶顶低速堵塞区域减小,增强了转子叶顶的流通能力,达到扩稳的目的;引气位置和引气质量流量对转子稳定性的影响具有交互作用,在0.5%和1.0%引气质量流量比下,随着引气位置的后移,转子稳定工作裕度逐渐减小,在1.5%引气质量流量比下,随着引气位置的后移,转子稳定工作裕度却呈现先增大后减小的趋势;引气位置在20%叶片叶顶轴向弦长(C)处时,随着引气质量流量的增加,转子稳定工作裕度先增大后减小,而引气位置在60%C和100%C处时,随着引气质量流量的增加,转子稳定工作裕度逐渐增大。     

竖直矩形窄通道内沸腾换热特性及液滴夹带的实验研究

对通道尺寸为1 400 mm×250 mm×2.75 mm的竖直矩形窄通道内沸腾换热特性及液滴夹带进行了实验研究,分析了不同液位、加热蒸汽流量、补液温度下换热性能以及液滴夹带的变化规律。实验结果表明：随着初始液位高度的提高会出现一个拐点,在到达拐点后,继续提高初始液位以及增加补液量将不会改变最终液位的高度;实验段的传热系数随着液位的升高先增大,并在拐点附近达到最大值,随后减小;在相对液位低时,未出现液滴夹带,而当液位逐渐接近液位拐点时,通道出口逐渐出现液体,而夹带量在液位达到拐点后迅速上升;随着加热蒸汽流量的提高,换热量的增加使沸腾换热更加剧烈,传热系数和带液量显著增大;补液温度越高,传热系数越大,但是补液温度对带液量无明显影响。     

低雷诺数下不同顶角三棱柱体绕流受力和尾涡脱落机制

为研究三棱柱体绕流特性,采用直接数值模拟方法,对雷诺数为100时顶角为15°~165°的三棱柱的二维绕流问题进行了数值模拟,并与经典的圆柱绕流进行对比分析。结果表明,随着顶角度数的增大,三棱柱体受到的时均阻力不断增大,而升力均方值先增大后减小,在顶角为60°时达到最大值(0.31);随着顶角度数的增大,尾涡强度逐渐增大,泄涡频率先增大后减小,在顶角为60°时,泄涡频率最大;前尾涡脱落产生的中心点与鞍点随新尾涡的产生依次消失,而新的尾涡的中心点与鞍点同时逐渐形成。     

襟翼翼缝相对宽度对翼型气动性能影响研究

以NACA0018为基准翼型,采用Fluent数值模拟的方法,对比研究了襟翼相对长度和翼缝相对宽度对翼型流场结构及升、阻力特性的影响;分别选取襟翼相对长度分别为0.2、0.3和0.4和翼缝相对宽度分别为1.0%、1.5%以及2.0%,着重分析翼缝相对宽度对翼型气动性能的影响。数值结果表明,由于襟翼对翼型周围主涡发展和变化的影响,不仅改善了翼型的失速特性,同时也提高了翼型的气动性能。襟翼翼型的失速攻角在此次研究范围内均大于基准翼型,在攻角小于失速攻角时,襟翼翼型的升力系数均小于基准翼型,阻力系数均高于基准翼型,但升力系数的最大值均高于基准翼型;随着襟翼相对长度增大,翼型临界攻角逐渐减小;在攻角接近翼型失速攻角时,升力系数先增大后减小;襟翼长度相同时,随着翼缝相对宽度的增大,升力系数逐渐减小。在翼缝流体入口端,主翼末端存在一个涡,随着翼缝相对宽度增大,该涡流范围逐渐扩大;在襟翼前端有局部的压力升高,随着翼缝相对宽度增大,该局部高压范围扩大。     

核电汽轮机末级空心静叶抽吸除湿研究

采用粒子输运模型对某核电汽轮机低压缸末级空心静叶栅内的水滴运动轨迹和沉积分布进行三维数值计算,得出水滴沿静叶相对叶高和相对叶宽的沉积量,并讨论不同除湿槽几何参数对空心静叶抽吸除湿性能的影响.结果表明:水滴主要沉积在空心静叶压力面的上半部分,少量沉积在吸力面进口边和上端壁表面.压力面上的除湿槽应当在工艺许可的条件下尽量靠近出口边,吸力面上的除湿槽应尽量和压力面除湿槽开设在同一压力水平上;除湿槽宽度增大时并不一定有利于提高除湿效率,最佳宽度与汽流速度和抽吸压比有关;除湿槽角度应在工艺许可的条件下应尽量小一些.研究结果对后续的试验研究及工程设计具有指导意义.     

Effects of water suction on water film tearing at trailing blade edges

Using air‐to‐water film two‐phase flow test equipment with a high‐speed camera, water suction from the suction slot in front of stationary blade was experimentally carried out. The water film moved along the stationary blade surface under the action of the high speed airflow. Under the suction conditions, the tearing of the water film at the trailing edges of a hollow stationary blade were studied. The results show that the water film flowing on the stationary blade surface would immediately break into some silky rivulets or sub‐film following the suction slot, if the water in the film was partially drawn off the suction slot. The silky rivulets or sub‐films first slightly piled up at the trailing edge of the stationary blade, and then tore into drops of different shapes and diameters, and moved with the air flow. The larger drops, formed due to further tearing, broke up into finer droplets due to the action of high speed flow air. The number of water droplets gradually increased, and the diameter of water drops gradually decreased. © 2005 Wiley Periodicals, Inc. Heat Trans Asian Res, 34(6): 380–385, 2005; Published online in Wiley InterScience ( www.interscience.wiley.com ). DOI 10.1002/htj.20077     

Efficiency enhancement in transonic compressor rotor blades using synthetic jets: A numerical investigation

Several passive and active techniques were studied and developed by compressor designers with the aim of improving the aerodynamic behavior of compressor blades by reducing, or even eliminating, flow separation. Fluidic-based methods, in particular, have been investigated for a long time, including both steady and unsteady suction, blowing and oscillating jets. Recently, synthetic jets (zero mass flux) have been proposed as a promising solution to reduce low-momentum fluid regions inside turbomachines. Synthetic jets, with the characteristics of zero net mass flux and non-zero momentum flux, do not require a complex system of pumps and pipes. They could be very efficient because at the suction part of the cycle the low-momentum fluid is sucked into the device, whereas in the blowing part a high-momentum jet accelerates it. To the authors’ knowledge, the use of synthetic jets has never been experimented in transonic compressor rotors, where this technique could be helpful (i) to reduce the thickness and instability of blade suction side boundary layer after the interaction with the shock, and (ii) to delay the arising of the low-momentum region which can take place from the shock-tip clearance vortex interaction at low flow operating conditions, a flow feature which is considered harmful to rotor stability. Therefore, synthetic jets could be helpful to improve both efficiency and stall margin in transonic compressor rotors. In this paper, an accurate and validated CFD model is used to simulate the aerodynamic behavior of a transonic compressor rotor with and without synthetic jets. Four technical solutions were evaluated, different for jet position and velocity, and one was investigated in detail.     

汽轮机静叶缝隙去水效率的实验研究

在气－水膜两相流动试验装置上对平板空心叶片去湿缝隙的去水效率进行了试验研究。分析讨论了气流速度、叶片上水膜流量、抽吸压差、缝隙宽度及角度对缝隙去水效率的影响,确定了叶片去水缝隙的合理形状及尺寸     

汽轮机空心静叶去湿缝隙结构的研究

在空气-水膜两相流动试验装置上,试验研究了去湿缝隙几何形状和尺寸与缝隙去水效率之间的关系,得到了缝隙角度、宽度与去水效率的关系曲线;分析了空心静叶去湿缝隙的抽吸过程和机理;讨论了缝隙抽吸对叶栅通道内主流场的影响。结果表明：小的缝隙角度可以提高缝隙的去水效率;存在一个去水效率较低的缝隙宽度范围,在本试验条件下,相应去水效率较低的缝隙宽度为1．0～1．5mm;另外,将缝隙进口前端边缘加工成带有半径为1mm的过渡圆角,可以将缝隙去水效率提高5％以上。在此基础上,提出了空心静叶去湿缝隙的基本设计原则以及合理的缝隙结构形状与尺寸。     

Aerodynamic Performance Improvement of a Highly Loaded Compressor Airfoil with Coanda Jet Flap

Coanda jet flap is an effective flow control technique,which offers pressurized high streamwise velocity to eliminate the boundary layer flow separation and increase the aerodynamic loading of compressor blades.Traditionally,there is only single-jet flap on the blade suction side.A novel Coanda double-jet flap configuration combining the front-jet slot near the blade leading edge and the rear-jet slot near the blade trailing edge is proposed and investigated in this paper.The reference highly loaded compressor profile is the Zierke&Deutsch double-circular-arc airfoil with the diffusion factor of 0.66.Firstly,three types of Coanda jet flap configurations including front-jet,rear-jet and the novel double-jet flaps are designed based on the 2D flow fields in the highly loaded compressor blade passage.The Back Propagation Neural Network(BPNN)combined with the genetic algorithm(GA)is adopted to obtain the optimal geometry for each type of Coanda jet flap configuration.Numerical simulations are then performed to understand the effects of the three optimal Coanda jet flaps on the compressor airfoil performance.Results indicate all the three types of Coanda jet flaps effectively improve the aerodynamic performance of the highly loaded airfoil,and the Coanda double-jet flap behaves best in controlling the boundary layer flow separation.At the inlet flow condition with incidence angle of 5°,the total pressure loss coefficient is reduced by 52.5%and the static pressure rise coefficient is increased by 25.7%with Coanda double-jet flap when the normalized jet mass flow ratio of the front jet and the rear jet is equal to 1.5%and 0.5%,respectively.The impacts of geometric parameters and jet mass flow ratios on the airfoil aerodynamic performance are further analyzed.It is observed that the geometric design parameters of Coanda double-jet flap determine airfoil thickness and jet slot position,which plays the key role in supressing flow separation on the airfoil suction side.Furthermore,there exists an optimal combination of front-jet and rear-jet mass flow ratios to achieve the minimum flow loss at each incidence angle of incoming flow.These results indicate that Coanda double-jet flap combining the adjust of jet mass flow rate varying with the incidence angle of incoming flow would be a promising adaptive flow control technique.     

Numerical simulation of a new hollow stationary dehumidity blade in last stage of steam turbine

As a result of adopting saturation steam and long blade, problems of water erosion of last stage blade for steam turbine become more prominent. In order to improve the operation reliability and efficiency of steam turbine, it is necessary to investigate the nonequilibrium condensing wet steam two phase flow and the dehumidity method. A wet steam model with user defined function based on FLUENT software was investigated to simulate the steam condensing flow in the cascades. The simulation consequences show that the pressure variations in simulation depict a good agreement with the experiment data. On the basis of the discrete phase model simulation results and experiment data, the efficiency of existing dehumidity blade with suction slot was calculated. A new stationary dehumidity blade was designed to elevate the dehumidity efficiency: the efficiency in the suction surface was increased by 21.5%, and that in the pressure surface was increased by 12.2%.     

带后置蜗壳的斜流叶轮机匣处理扩稳研究

针对小型高速斜流叶轮的机匣处理进行了实验研究与数值模拟分析.实验结果表明,所设计的机匣处理结构可以有效地扩大斜流叶轮的工作范围.采用并行计算技术,对包括斜流叶轮机匣处理以及蜗壳在内的整机流场进行了数值模拟,揭示了机匣处理扩稳的机理,机匣处理结构将叶片顶部区域的低能流体抽吸进入处理槽,从叶片通道内吸力面侧区域流出周向槽,射入转子通道,吹除该区域的低能气团阻塞,改善了转子叶片叶顶区域的气流流动状况,推迟失速的发生.     

小型离心压气机径向扩压器复杂涡系结构分析

对某小型离心压气机进行详细数值模拟,构建径向扩压器复杂涡系结构模型,重点分析设计、堵塞、失速工况下径向扩压器内部复杂涡系结构。研究表明：径向扩压器内部涡系结构主要包括前缘涡、两个通道涡（压力面侧通道涡与吸力面侧通道涡）以及喉部涡;主叶片吸力面的前缘涡是机匣侧低能流体在展向与流向压力梯度作用下形成的,喉部涡是吸力面侧通道涡沿分流叶片前缘的回流与前缘涡构成的;喉部涡在喉部的堆积是导致径向扩压器失速的原因,径向扩压器喉部的激波则是堵塞的原因;随流量的减小,前缘涡的涡核越向相邻主叶片压力面迁移。