NUMERICAL CALCULATIONS OF GASEOUS REACTING FLOWS IN A MODEL OF GAS TURBINE COMBUSTORS

This paper describes the numerical calculations of gaseous reaction flows in a model of gas turbine combustors. The profiles of hydrodynamic and thermodynamic patterns in a three-dimensional combustor model are obtained by solving the governing differential transport equations. The well-established numerical prediction algorithm SIMPLE, the modified k-ε turbulence model and k-ε-g turbulent diffusion flame model have been adopted in computations. The β function has been selected as probability density function. The effect of combustion process on flow patterns has been investigated. The calculated results have been verified by experiments. They are in remarkably good agreement.

EXPERIMENTAL MEASUREMENT AND NUMERICAL SIMULATION FOR FLOW FIELD AND FILM COOLING EFFECTIVENESS IN FILM-COOLED TURBINE

Numerical simulation of three-dimensional flow field and film cooling effectiveness in film-cooled turbine rotor and stationary turbine cascade were carried out by using the k- ε turbulence model, and the predictions of the three-dimensional velocities were compared with the measured results by Laser-Doppler Velocimetry （LDV）. Results reveal the secondary flow near the blade surface in the wake region behind the jet hole. Compared with the stationary cascade, there are the centrifugal force and Coriolis force existing in the flow field of the turbine rotor, and these forces make the three-dimensional flow field change in the turbine rotor, especially for the radial velocity. The effect of rotation on the flow field and the film cooling effectiveness on the pressure side is more apparent than that on the suction side as is shown in the computational and measured results, and the low film cooling effectiveness appears on the pressure surface of the turbine rotor blade compared with that of the stationary cascade.

Numerical simulation of icing effects on static flow field around blade airfoil for vertical axis wind turbine

Icing on blade surface of the straight-bladed vertical axis wind turbine(SB-VAWT)set in cold regions is a serious problem.To study the performance effects of icing on SB-VAWT,numerical simulations were carried out on the ice accretion on NACA 0015 airfoil which was always used for blade airfoil of SB-VAWT by CFD methods based on 2D steady incompressible N-S Equation.The morphology and procedure of icing on blade airfoil were obtained under different wind speeds,attack angles of blade and water flow flux in wind.The static flow fields,especially the static pressure fields around blade airfoil with or without icing on it were computed.The aerodynamic characteristics including the lift and drag force coefficients of blade airfoil were also calculated.The results indicated that icing caused the static pressure field changed greatly and led to the increasing of drag force and reducing the aerodynamic performance.

Simulation of Gas Flow Field in Laval Nozzle and Straight Nozzle for Powder Metallurgy and Spray Forming

Gas flow field in nozzles and out of nozzles was calculated for Laval orifice and straight orifice nozzles. The results showed that the flow generated by the Laval nozzle had a higher exit velocity in the vicinity of the nozzle, in comparison with that of the straight nozzle, that is to say, a Laval nozzle was more efficient than a straight one in disintegrating the melt stream and was apt to produce finer powders. The flow generated by the Laval nozzle was less convergent and the velocity gradient along the radial direction was more moderate than that of a straight nozzle, which could contribute to a broad distribution of melt particles. According to their flow characteristics, the Laval nozzle was reckoned as a better choice of producing larger spray-formed billets.

Effect of atomization gas pressure variation on gas flow field in supersonic gas atomization

In this paper, a computational fluid flow model was adopted to investigate the effect of varying atomization gas pressure (P0) on the gas flow field in supersonic gas atomization. The influence of P0 on static pressure and velocity magnitude of the central axis of the flow field was also examined. The numerical results indicate that the maximum gas velocity within the gas field increases with increasing P0. The aspiration pressure (ΔP) is found to decrease as P0 increases at a lower atomization gas pressure. However, at a higher atomization gas pressure increasing P0 causes the opposite: the higher atomization gas pressure, the higher aspiration pressure. The alternation of ΔP is caused by the variations of stagnation point pressure and location of Mach disk, while hardly by the location of stagnation point. A radical pressure gradient is formed along the tip of the delivery tube and increases as P0 increases.

IDDES方法模拟风切变下大型水平轴风力机流场特性

为研究风切变条件下大型水平轴风力机流场特性,以NH 1500 kW大型水平轴风力机为研究对象,运用计算流体力学中模拟流场精度较高的IDDES(改进延迟分离涡)方法,分析流场内瞬时速度分量、脉动速度和风力机输出功率。结果表明:风轮平面周围流场速度波动大,轴向速度在风轮旋转边界以外的区域会增大,在旋转边界以内的区域会亏损;脉动风速频谱特性在低频区与风轮转频的整数倍相关,风力机功率呈余弦形式输出并满足湍流谱特性。

抽水蓄能机组水轮机工况启动过程内部流场分析

本文采用CFD数值模拟的方法,模拟计算了抽水蓄能机组在水轮机工况启动过程内部流场特征。得到了在活动导叶开启过程中的速度、压力随时间的瞬态分布规律,讨论了蓄能机组开启过程中外特性的变化曲线。结果表明:活动导叶的开启规律可以大体分为五个阶段。活动导叶的开启规律是先缓慢开启,然后以较快的速度关闭,最后再保持到空载的开度,从第四阶段,导叶再逐渐打开直到额定开度。转轮扭矩和机组流量呈现出先增大后减小的趋势,当导叶逐渐打开时,转轮扭矩和机组流量再逐渐上升。本文为研究蓄能机组水轮机工况下启动过程的内部流动变化提供了参考依据,同时对提高水轮机工况的启动稳定性具有重要意义。

基于气固两相流数值模拟的下鼻甲切除虚拟手术效果评价研究

运用数值模拟的方法探讨不同的下鼻甲切除虚拟手术方案的效果。为一位患慢性肥厚性鼻炎的患者重建了真实鼻腔模型A,采用虚拟手术的方法修改模型A的几何结构,分别根据双侧下鼻甲下缘水平切除术、下鼻甲后端切除术以及下鼻甲下缘及后端切除术得到了鼻腔模型B、模型C和模型D。并在上述四个模型内分别展开数值模拟,对比分析其流场分布和颗粒物的沉积比与沉积形式。模型A中左侧鼻腔的气流速度较快,左右鼻腔的气流分布差异也较大,模型B和模型D的最大气速和左右鼻腔的流速差异均有减小。在不同流量条件下,模型B和模型D的鼻腔进出口压降与模型A相比均降低。较大粒径的颗粒在鼻腔模型内的沉积比显著降低,8μm时模型B和模型D的沉积比分别比模型A降低了14.5%和14.8%,10μm时分别降低了14%和14.5%。模型C的流场分布和颗粒物的沉积特性与模型A相差不大。模型B和模型D可以更好地降低鼻阻力,减轻左右鼻腔流场差异引起的不舒适感,降低颗粒物在鼻腔内的沉积比,尤其减少了鼻中隔、鼻咽和咽喉区域的颗粒物沉积。

基于大涡模拟方法的三维旋转爆轰流场结构研究

为研究环形燃烧室中边界层、黏性、湍流模拟方法对旋转爆轰流场结构的影响,采用开源计算流体动力学软件OpenFOAM,以氢气为燃料、空气为氧化剂,基于大涡模拟(Large Eddy Simulation,LES)方法、RANS方法、Euler方法,分别结合滑移和无滑移边界,对三维旋转爆轰发动机模型进行数值模拟,分析对比不同计算方法下旋转爆轰流场结构。着重讨论以LES方法得到的流场结构。研究结果表明:当采用滑移边界时内、中、外截面的流场温度无太大差异,当采用无滑移边界时内外壁面温度高于中间截面,边界层会影响近壁区域气体的流动速度,导致内外壁面爆轰波高度低于中间截面,还会影响燃烧产物的流动状态轴向截面上爆轰波波头产生变形;不同湍流计算方法得到的旋转爆轰流场结构存在相似性,黏性是影响旋转爆轰流场结构的主要原因。研究结果对于揭示边界层和黏性对旋转爆轰的影响机制具有一定的科学意义。

某F级燃气轮机燃烧与NO_(x)排放特性研究

为了给我国F级燃气轮机燃烧系统的燃烧调整与自主升级提供技术参考,以某F级燃气轮机环管燃烧室单筒为三维物理模型,采用Realizable k-ε湍流模型与小火焰生成流形(flamelet generated manifold,FGM)燃烧反应模型,研究了过量空气系数、主旋流叶片偏转角度及值班燃料占比等因素对燃烧室单筒内的温度分布规律、燃烧污染物NO_(x)的生成与排放特性的影响。结果表明:随着燃烧室单筒入口过量空气系数的增加,燃烧室单筒出口的平均温度与最大温度均下降,出口温度分布系数(out-let temperature distribution factor,OTDF)略微上升,出口温度分布均匀性降低,但NO_(x)排放量呈下降趋势;适当增大主旋流叶片偏转角度,可以降低燃烧室单筒内及过渡段出口截面的最高温度并提升温度均匀性,但出口NO_(x)排放量则呈先急剧下降后缓慢上升的趋势;在总燃料流量不变的情况下,值班燃料占比(质量分数)从4%增大到8%时,燃烧室单筒出口温度水平的变化很小,但会导致NO_(x)排放量明显增加。

涡轮叶片气热耦合壁温及压力分布计算与分析

针对气冷涡轮叶片建立了耦合分析数值模拟计算平台,采用气热耦合的方法,对径向气冷MARKⅡ型叶片进行三维气热耦合数值模拟。分析了该内冷涡轮叶片的多场耦合特性,并将计算结果与试验值进行对比。对比结果表明:湍流模型的选择影响叶片表面的温度分布,但对叶片表面压力分布影响较小;在选择的6种湍流模型中,SSTk-ω湍流模型对该流场状态模拟的效果较好,叶片表面温度和压力与试验结果最接近,满足工程上的计算要求。考虑涡轮进口总温径向不均匀时,会在叶片尾缘形成局部高温区,增加了叶身的温度梯度,可适当改进冷却方式,以提高叶片强度。

计算域尺寸对风力机翼型数值模拟的影响

计算域尺寸的选取对风力机翼型数值模拟至关重要,文章通过建立13种不同尺寸的计算域模型,采用雷诺时均N-S方程和SST k-ω湍流模型,在雷诺数为3×10^(6)的条件下,分析不同计算域尺寸对NACA63-418翼型升力系数、阻力系数、压强系数和流场分布规律的影响。计算结果与实验结果的对比表明,风力机翼型数值模拟的计算域最小尺寸推荐为距离翼型前缘14倍弦长,距离翼型后缘27倍弦长,距离两侧边界15倍弦长。

重燃多级轴流压气机级间引气方式对流场影响的数值研究

本文以某重型燃气轮机多级轴流压气机的3.5级作为研究对象,对源项及周向槽引气方式下的压气机性能和局部流场进行了数值研究。结果表明:两种引气方式计算得到的主流性能参数在大部分工况下都具有较好的一致性,级数越多两者计算结果的误差越小;两种引气方式对70%叶高以上主流流场的预测偏差较大,相对而言,周向槽引气的预测结果更合理;大部分工况下,主流流场参数对引气角度并不敏感,引气对主流的影响只存在于下游,难以向上游传递。

船用燃气轮机进气道结冰位置研究

针对船用燃气轮机进气道结冰问题,本文采用数值模拟的方法开展了风速、进气风向角对船用燃气轮机进气道结冰的影响研究,分析了不同风速、进气风向角下进气道内流场、水撞击系数以及结冰规律。研究结果表明:进气道内主要结冰位置为进气竖井弧形区域以及进气竖井和稳压箱连接部分的渐缩段,且随着风速的增高,结冰位置越集中;低风速工况的水收集系数以及平均结冰系数大于高风速工况,液滴在进气道内更易结冰;当进气风向角为135°时,进气道内积冰最为严重。

主燃孔方案对回流燃烧室流动影响的数值研究

为探究主燃孔开孔方案对辅助动力装置回流燃烧室流动特性的影响,开展5种主燃孔开孔方案的矩形回流燃烧室冷态流场数值模拟研究,数值模拟方法通过粒子图像测速试验数据进行了有效性验证。结果表明:燃烧室主燃区流场形成了大尺度双涡流动结构,有利于火焰稳定。外环主燃孔射流穿透深度明显大于内环主燃孔射流,因此对流场影响更大。外环主燃孔数目越多,孔径越小,主燃区沿轴向和展向的尺寸都变大。主燃孔排列方式对主燃区流场结构影响很小,但对中间区流场影响显著。

中心分级贫油直喷燃烧室冷态流场特性

为了研究中心分级贫油直喷燃烧室冷态流场特性及头部结构参数对中心回流区的影响,采用数值模拟方法对不同结构参数下的冷态流场开展对比研究,并对基准方案进行了试验验证。结果表明:副模收敛角度以及喷嘴轴向位置对回流区影响较小,副模旋流叶片角度以及主副模头部径向间距对回流区影响较大。随着副模旋流叶片角度增大,副模出口旋流加强,引起出口气流张角增大,使得中心回流区体积扩大;随着主副模头部径向间距增加,削弱了主副模出口气流在切向方向上的相互影响,主模出口气流得以充分发展,中心回流区体积扩大。

燃气轮机贫预混多旋流组合燃烧室头部结构设计

根据势流理论对5种不同结构的多头部旋流器进行了讨论,从联焰、壁面温度、流场的角度选取其中3种形式的方案进行进一步的数值模拟研究,利用计算流体方法考察其主级和中心值班级燃烧器旋向对燃烧特性的影响。结果表明:主级采用不同旋向时有利于联焰,但非对称流场会出现热斑,对满负荷状态下NO_(x)污染物以及火焰筒冷却带来影响;当仅有值班级旋流与主旋旋转方向不一致时,郁金香形状火焰较长;当全部旋流器(主旋加值班级)的旋向相同时,仅有一个郁金香形火焰;当相邻两主旋旋转方向不同时,产生稳定的一对郁金香形火焰与一对开火焰。

9F级燃机选择性催化还原脱硝数值模拟研究与应用

以某9F级燃机余热锅炉为研究对象,对燃机出口烟道至催化剂层烟气流场数值模拟进行研究,得到了单层催化剂、两层催化剂、两层催化剂+均布板3种结构下烟气流场情况。结果表明:原结构第一层换热器前存在的扩张烟道距离短、扩张角度大,燃机出口高速旋流烟气进入大面积静置流域时,短距离内来不及均匀地冲刷整个大截面并消散惯性旋流,导致第一层换热器入口截面烟气流场均匀性较差;新增一层催化剂后,流场分布与单层催化剂时基本相同,且两层催化剂时首层催化剂入口流场分布均匀性略优于单层催化剂,这是因为新增一层催化剂相当于增加了一层流场阻流件,对烟气起到了阻流作用;通过在入口烟道加装导流板,可改善第一层换热器入口流场均匀性,截面流速Cv值下降至21.3%,表明导流板对后续烟道流场分布起到了一定的改善作用。

池壁效应对水平轴潮流涡轮水动力性能影响分析

为了分析池壁效应对水平轴潮流涡轮水动力性能的影响,本文采用数值仿真与模型试验的方式测试直径300 mm潮流涡轮的水动力性能,并对数值仿真方法进行验证;采用Bahaj修正方法与数值仿真方法对不同流域、流速下涡轮的能量转换效率以及阻力系数进行对比,进一步分析池壁效应对涡轮桨盘处以及尾流区域流场的影响。研究结果表明:池壁效应对水平轴潮流涡轮的水动力性能影响明显,其对能量转换效率影响伴随尖速比的增加逐渐增大;池壁效应对潮流涡轮桨盘处的轴向流速以及流场分布影响较小,但对潮流涡轮尾流区轴向速度恢复影响明显。研究结果可为水平轴潮流涡轮水动力性能的数值仿真研究与试验提供相关数据以及参考。

Experimental and Numerical Study of Gas Dynamics of Exhaust Pipe of Gas Turbine Unit

A few geometrical configurations of exhaust pipe of marine gas turbine unit were investigated experimentally in NPP'Mashproeykt' (Nikolaeyv, Ukraine) and numerically with objective of solver verification and to determine the optimal configuration with minimal level of total pressure loss.