锅炉过热器进口集箱三通区域静压分布的数值模拟及三通的结构改进

为解决过热器超温爆管问题,根据电站锅炉过热器带三通集箱的结构特点,采用数值模拟方法对采用径向引入方式的过热器进口集箱三通区域的静压分布和流动规律进行了研究,并在此基础上对三通区域结构进行了改进.结果表明:三通区域集箱中存在涡流区,使该区域的静压变低,导致布置在该区域的支管蒸汽流量减少;适当增大三通区域集箱内径可提高集箱涡流区的静压,但当三通区域集箱内径增大到一定程度后,继续增大三通区域集箱内径,集箱涡流区的静压已不再有明显升高.     

电站锅炉三通集箱系统流量分配的数值模拟

针对大容量电站锅炉中过热器和再热器集箱的径向引入引出三通结构进行了数值模拟,并运用Fluent软件,对稳态工况下径向引入引出三通结构的静压分布特点、流动机理、三通附近区域的流态对流量分配的影响进行了研究.结果表明:强三通效应在主母线方向、侧母线方向体现出不同的特征,主要原因是在三通区域存在3个明显的回流区,其共同作用决定了三通效应的影响模式;分流三通结构在三通附近受回流区的影响,Eu值均出现极小值,此处支管的流量驱动依赖于汇流集箱的压差补充,因而是危险区域,但其影响范围在2D内,故在布置支管时应考虑避开这一危险区.     

管组集箱采用三通结构引入引出对锅炉再热器热偏差的影响

再热器蒸汽侧压降一般很小,集箱中的静压分布将是决定并联管屏流量分配的重要因素.当集箱引入管为三通结构时,在三通区域的集箱中存在涡流区,使该区域的集箱静压大大下降,造成这部分管屏流量偏小,热偏差增大,甚至导致超温爆管.本文根据实炉再热器的出口汽温分布特征,以及三通管流场和静压分布的实验结果,分析了屏间热偏差产生的原因,并提出减小屏间热偏差的改进方向.     

电站锅炉过热器、再热器集箱静压分布的数值研究

利用数值模拟的方法，研究了径向引入引出型分配、汇流集箱系统的静压分布规律。为了消除计算中伪扩散的影响，选用了QUICK格式。数值计算结果表明：在三通附近，气流的变化非常强烈，在远离三通的区域．气流逐渐平稳。在分配集箱进口三通的两侧存在2个涡流区，正对三通中心线的支管处静压最高，远离三通的区域，静压分布与轴向引入引出方式规律基本一致。利用该方法计算了某电厂锅炉末级再热器的流量分配和热偏差情况，与实测结果相吻合。图6表1参2     

T型进口三通对分配集箱流量分配的影响

Ｔ型进口三通的布置方式分配集箱中的流量分配有着严重的影响。该文对三通附近涡流区中的集箱静压分布和支管入口阻力系数进行了深入的实验研究。     

三通集箱过热器压力分布与流量分配的数值模拟

为了解三通结构对过热器流量分配的影响从而解决三通集箱过热器的爆管问题,利用Fluent软件对过热器模型进行了数值模拟,研究了三通结构集箱过热器内的静压分布、速度分布、各支管流量分配及各支管入口处流体的流速分布和静压分布.结果表明:三通结构附近流体的压力低且速度大,而远离该区域的流体则压力高且速度小;三通中涡流区域的支管入口有小涡流,而其他区域的支管入口没有出现小涡流;集箱内涡流下部的支管流量偏小,正对集箱入口处的支管流量最大;将第7管屏和第11管屏的入口形状改为圆形,改造后支管的流量明显增大.     

电站锅炉三通集箱流场的数值研究

根据电站锅炉三通集箱系统的结构特点,采用基于三维实体模型的建模方案,对径向引入引出集箱系统的流场分布进行了数值模拟。采用FLUENT软件分析了集箱流场的分布特点及受热面沿程阻力对集箱速度、静压分布的影响,详细讨论了三通结构、受热面沿程阻力对受热面流量分配的影响。研究结果表明,集箱流场呈三维分布,分为径向引入管下游的冲击射流区和周围的强迫对流区,三通结构直接影响集箱的速度分布;受热面的流量分配直接受三通结构的影响,沿程阻力影响受热面流量偏差的大小。     

电站锅炉再热器带"三通"集箱静压分布的数值模拟及受热面热偏差计算

为解决再热器超温爆管问题,采用标准K-ε方程的湍流模型进行数值模拟,得到了有支管和无支管的再热器带"三通"集箱内的速度矢量和静压分布.在此基础上编写了较为通用的电站锅炉受热面热偏差计算程序,并应用该程序计算了2个不同结构再热器的屏间热偏差.结果表明:为了减少受热面因热偏差过大而发生超温爆管的情况,应在设计时尽量使管屏(子)避开集箱"三通"涡流区,或者将集箱"三通"避开烟温高峰区布置.此热偏差计算程序可以用于不同容量机组的多种结构和类型的受热面热偏差计算,适用于集箱轴向、径向引入引出的布置方式,可用于大型电站锅炉过热器及再热器的优化设计.     

分配集箱静压分布参数Cf值的理论分析

在分配集箱中取微元控制体，通过建立质量守恒方程和动量守恒方程，明确了参数Ｃｆ的物理意义。依据Ｃｆ取值范围，描述了分配集箱静压分布和动量交换控制为主、动量交换与摩擦阻力竞相影响、摩擦阻力控制为主３种情形与Ｃｆ的关系，理论分析与前人试验结果相吻合。同时，对采用我国水动力计算标准方程给出的Ｃｆ＝１．２４计算分配集箱静压分布时，给出了分配集箱长径比的限制。不同的长径比，集箱内静压分布呈现动量交换控制或动量     

直喷式柴油机燃油撞壁特性及混合气形成研究

应用STAR-CD软件对燃油撞壁进行三维数值模拟,重点研究入射角度、环境压力和涡流比对撞壁特性和混合气形成的影响.结果表明,撞壁后燃油的二次雾化对燃油蒸发具有重要作用.随着壁面入射角度的增大,壁面油膜扩展面积增大,油膜从长叶形向扇形变化.随着环境压力的增高,燃油分布范围明显减小,但燃油堆积量和浓混合气的面积都会进一步减小,形成相对稀薄的混合气.涡流对燃油的影响主要发生在撞壁之后,随着涡流比的增大,形成大范围的稀混合气.涡流比过高,相邻油束的混合气将会发生干涉,造成燃烧质量下降.     

Effects of rim location, rim height, and tip clearance on the tip and near tip region heat transfer of a gas turbine blade

Effects of the rim height and the tip gap clearance on the heat transfer coefficients on the blade tip and near tip regions were measured with two different rim geometries. The heat transfer coefficient distributions were measured using the transient single color capturing liquid crystals technique. Rims were located along (a) the pressure and the suction side (full-rim case) and (b) the suction side of the blade tip (suction side rim case). The rim heights were (a) 2.1%, (b) 4.2%, and (c) 6.3% and the blade tip gap clearances were (a) 1.0%, (b) 1.5%, and (c) 2.5% of the blade span. Tests were performed on a five-bladed linear cascade placed in a blowdown facility. The overall pressure ratio, inlet total pressure to exit static pressure, was 1.2, and the Reynolds number based on the exit velocity and the axial cord length was 1.1 × 10⁶. The turbulence intensity level at the cascade inlet was 9.7%, and the inlet and exit Mach number were 0.25 and 0.59, respectively. It was found that higher rims reduce the heat transfer coefficients on the tip and shroud, but the reduction on the pressure and suction sides was not significant. The suction side rim case provided lower heat transfer coefficients on the blade tip and near tip regions than the full-rim case.     

Two-Phase Heat Sinks with Microporous Coating

To minimize flow boiling instabilities in two-phase heat sinks, two different types of microporous coatings were developed and applied on mini- and small-channel heat sinks and tested using degassed R245fa refrigerant. The first coating was epoxy based and was sprayed on heat sink channels, while the second coating was formed by sintering copper particles on heat sink channels. Minichannel heat sinks had overall dimensions 25.4 mm × 25.4 mm × 6.4 mm and 12 rectangular channels with a hydraulic diameter 1.7 mm and a channel aspect ratio of 2.7. Small-channel heat sinks had the same overall dimensions, but only three rectangular channels with hydraulic diameter 4.1 mm and channel aspect ratio 0.6. The microporous coatings were found to minimize parallel channel instabilities for minichannel heat sinks and to reduce the amplitude of heat sink base temperature oscillations from ～6°C to slightly more than 1°C. No increase in pressure drop or pumping power due to the microporous coating was measured. The minichannel heat sinks with porous coating had on average 1.5 times higher heat transfer coefficient than uncoated heat sinks. Also, the small-channel heat sinks with the “best” porous coating had on average 2.5 times higher heat transfer coefficient and the critical heat flux was 1.5 to 2 times higher compared with the uncoated heat sinks.     

溢流口结构对石膏旋流器分离性能的影响

通过试验研究了溢流口结构参数对石膏旋流器生产能力、分离效率及分流比等工艺指标的影响.结果表明:随着溢流管插入深度的增加,石膏旋流器的分离效率和分流比呈先升高后降低的趋势,其生产能力则呈相反的变化趋势,存在一个最优的插入深度值;随着溢流管内径的增大,石膏旋流器的分离效率和分流比均降低,而生产能力则提高;在溢流管壁厚约为18 mm时,石膏旋流器的分离效率和处理能力达到最大值.     

Experimental and Numerical Analysis on the Internal Flow of Supersonic Ejector Under Different Working Modes

Supersonic ejectors involve very complex phenomena such as interaction between supersonic and subsonic flows, shock trains, instabilities, which strongly influences the performance of supersonic ejector. In this study, the static pressure distribution along the ejector wall and Mach number distribution along the axis are used to investigate the internal flow field of supersonic ejector. Results indicate that when the back pressure is much less than the critical back pressure, there are two series of shock trains, and the change of the back pressure will not affect the flow field before the effective area section, so the entrainment ratio would remain constant. The second shock train moves further upstream and is combined with the first shock train to form a single shock train as the back pressure rises. When the back pressure is greater than the critical back pressure, the position of the shock train, the static pressure at its upstream and the entrainment ratio, will be affected. The “effective area section” in the mixing tube is obtained. The effective area section position moves downstream with the increase of the primary flow pressure, while it moves upstream with the increase of the secondary flow pressure. The entrainment ratio shows inversely proportional relationship with the effective section position. Besides, the first shock train length increases with the increase of primary flow pressure or secondary flow pressure. The critical back pressure represents direct proportional relationship to the first shock train length.     

多级离心泵首级叶轮内部流动的数值模拟

为了解多级离心泵首级叶轮内部流动特性,基于N-S方程和标准κ-ε湍流模型对三长三短复合叶轮和四长四短复合叶轮内部流动进行了数值模拟,获得了两种叶轮在额定工况及非额定工况下的内部流场分布并进行了分析。结果显示,四长四短叶轮可改善叶轮内部流场、提高叶轮吸力面压力,进一步阻止小流量下的脱流现象,有效提高了整个泵的扬程和效率及高效区。     

Numerical investigation of pressure drop characteristics of gas channels and U and Z type manifolds of a PEM fuel cell stack

Fluid flow manifold plays a significant role in the performance of a fuel cell stack because it affects the pressure drop, reactants distribution uniformity and flow losses, significantly. In this study, the flow distribution and the pressure drop in the gas channels including the inlet and outlet manifolds, with U- and Z-type arrangements, of a 10-cell PEM fuel cell stack are analyzed at anode and cathode sides and the effects of inlet reactant stoichiometry and manifold hydraulic diameter on the pressure drop are investigated. Furthermore, the effect of relative humidity of oxidants on the pressure drop of cathode are investigated. The results indicate that increase of the manifold hydraulic diameter leads to decrease of the pressure drop and a more uniform flow distribution at the cathode side when air is used as oxidant while utilization of humidified oxidant results in increase of pressure drop. It is demonstrated that for the inlet stoichiometry of 2 and U type manifold arrangement when the relative humidity increases from 25% to 75%, the pressure drop increases by 60.12% and 116.14% for oxygen and air, respectively. It is concluded that there is not a significant difference in pressure drop of U- and Z-type arrangements when oxygen is used as oxidant. When air is used as oxidant, the effect of manifold type arrangement is more significant than other cases, and increase of the stoichiometry ratio from 1.25 to 2.5 leads to increase of pressure drop by 527.3%.     

Experimental Investigations of the Three—Dimensional Flow in a Large Deflection Turbine Cascade with Tip Clearance

INTRoDUCTI0NThetipleakaeflowisnowrecognizedasanimpor-tantsourceoflossesinbothcompressorsandturbines,asasourceofcoolingprobleminturbinesandasourceofinstabilityincomPressorsandfans.Manyturbo-maChinimPellersarenotshroudedandtheleakaeflowthroughthetipgaPofthebladeisanunavoidablefaCtorwhichdeterioratestheperformance.Den-tonandCumpsty[1]melltionedabouttwodistinctandequallyimportantaspects.tothetipclearanceflows.First,thereisareducti0ninthebladeforce,there-fore,theworkdone.Thisoccursbecausethe…     

Experimental Investigation of Louver Cooling Scheme on Gas Turbine Stator

An experimental investigation has been conducted to investigate the film cooling performance of the louver scheme over the surface of a gas turbine stator using a transient thermochromic liquid crystal technique. A two-dimensional airfoil cascade has been employed during the study. The exit Reynolds number based on the true chord length is 1.5E5 and the exit Mach number is 0.23. Two rows of an axially oriented louver scheme are distributed on both suction and pressure sides in a staggered arrangement. The effect of hole location on the cooling performance is investigated for each row individually; then row interaction is investigated at four different blowing ratios ranging from 1 to 2 and a 0.9 density ratio. The detailed local performance distribution and the lateral-averaged normalized performance are presented over both sides of the vane in terms of heat transfer coefficient and cooling effectiveness. The louver scheme provides a better cooling performance compared with the similar cylindrical scheme of the same base diameter at the same cooling amount. The blowing ratio does not influence significantly the performance for the louver scheme due to the considerable decrease in the jet momentum that impedes the jet lift-off at exit. The location of the scheme exit has a high impact on the cooling performance as it affects the development of the boundary layer. The double injection on the pressure side provides a superior effectiveness due to the blockage of the mainstream by the coolant injected from the first row. The louver scheme provides higher net heat flux reduction, which suits the cooling capacity needed for the next generation of gas turbines.     

Thermal Characteristics in a Tube With Loose-Fit Perforated Twisted Tapes

Enhanced heat transfer and pressure loss in a tube with loose-fit perforated twisted tapes were experimentally investigated. The effects of the twist ratio and the hole diameter ratio were also described. A constant twisted tape width of 52 mm, which is lower than the tube inside diameter of 56 mm, was used in order to reduce excessive pressure drops associated with full-width twisted tape elements. The tests were conducted using the tapes with three different ratios of pitch length of twisted tape to inner diameter of tube (twist ratios = 2, 2.5, 3) and three different ratios of hole to inner diameter (diameter ratios = 0.0714, 0.107, 0.143) in a range of Reynolds number 4860 to 24,130 under uniform heat flux conditions. The experimental findings revealed that the Nusselt number, friction factor, and thermal performance factor increase with decreasing twist ratio and hole diameter ratio. The maximum value of thermal performance factor of 1.27 was achieved for the case at a twist ratio of 2 and a hole diameter ratio of 0.0714. Eventually, the experimental results of Nusselt number, friction factor and thermal performance factor were correlated, and the deviations determined for Nusselt number, friction factor, and thermal performance factor were within ±7%, ±8%, and ±6%, respectively.