共查询到19条相似文献,搜索用时 125 毫秒
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汽轮机低压进汽腔室设计的优劣对机组效率有明显的影响,其对效率的影响主要有两个因素,一是腔室本身的流动情况;二是腔室出口气流角与静叶的匹配情况。采用计算流体力学(CFD)方法模拟了基于不同设计方案进汽腔室的流场情况,并根据流场参数计算了第一级的级效率。研究表明,采用切向进汽方式,并且根据腔室出口气流角匹配静叶叶型,可以提高低压缸第一级叶片的效率,降低机组热耗。未来将会有越来越多的汽轮机采用切向进汽腔室,以提高机组的效率。 相似文献
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汽轮机高压缸进汽蜗壳的数值研究 总被引:1,自引:0,他引:1
文章采用商用计算流体动力学软件CFX,针对某高压缸进汽蜗壳进行了详细的数值研究,并对影响切向进汽蜗壳气动特性的因素进行了研究,结果表明:切向进汽方式具有优越的气动特性,其进汽蜗壳截面的收缩比、截面形状以及进口管横向间距均对切向进汽室气动特性影响较大。湍动能和总压损失系数随截面收缩比的增加逐渐减小并趋于平缓。截面形状和进口管横向间距对切向进汽室总压损失系数影响较小,但对出口处湍动能影响较大。 相似文献
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对采用静叶栅部分进汽的双列调节级进行不同负荷分配的气动性能分析研究,同时分析静叶栅不同局部进汽对级性能的影响。运用全三维数值方法对全周双列调节级模型计算模拟。分析结果表明,首列叶栅负荷比的变化直接影响整级的气动性能,首列叶栅负荷从80%下降到50%的过程中,级效率呈现先上升后下降的趋势,即双列调节级存在一个最佳的首列载荷分配值。同时研究首列静叶栅和第二列静叶栅部分进汽度的设计,经研究,第二列静叶栅部分进汽度与首列静叶栅部分进汽度接近时,双列调节级的气动性能最优。 相似文献
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具有部分进汽特性的汽轮机调节级,其动叶围带顶部汽封齿后的泄漏流动同主流的相互作用,不仅影响机组的气动性能和效率,而且对机组的安全稳定性也有一定影响。基于三维黏性可压缩的Navier-Stokes方程对某150MW汽轮机调节级进行了全三维的数值模拟,建立了安装汽封齿全周流动模型,对不同进汽度下的汽轮机调节级内部流场进行了数值研究。结果表明:处于进汽段的动叶栅其流量和动叶扭矩都比较大,汽封内部流动总体是按照从动叶前缘向后缘的流动;而处于非进汽段的动叶栅,内部汽体基本处于呆滞状态,甚至存在蒸汽对动叶的扭矩为负值的情况,汽封内的流动方向改变,从动叶后缘向前缘发展。随着部分进汽度的降低,泄漏比例则显著增大,而轮周效率显著降低。 相似文献
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《热力透平》2021,(2)
采用3种切向蜗壳设计方法对某50 MW机组高压进汽流道进行了切向设计,获得3种形式的切向蜗壳:切向等截面设计、等环量设计以及线性收缩设计。采用数值仿真方法对3种形式的切向蜗壳进行了气动分析,获得了切向蜗壳的气动性能、流场分布等。结果表明:3种形式切向蜗壳的气动性能各不相同,等截面切向蜗壳的总压损失最大,出口均匀性最差,而等环量和线性收缩切向蜗壳的总压损失更小,出口均匀性也更好。其中,等环量设计的总压损失和出口均匀性均为最优。对于汽轮机进汽流道,不同切向进汽设计方法会导致不同的截面积周向变化规律,进一步影响蜗壳的气动性能。因此,汽轮机进汽流道在进行切向设计之前有必要选择适合的切向进汽设计方法。 相似文献
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迷宫式静叶隔板汽封的数值模拟分析 总被引:1,自引:0,他引:1
采用数值模拟的方法,考虑迷宫式静叶隔板汽封,对某汽轮机级气动特性进行了计算和分析。重点考察了汽封通道内的蒸汽流动情况,分析了迷宫式汽封气动方面的优点和对叶片气动特性的影响,从而提出了一些有意义的结论和建议。 相似文献
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研究了大功率汽轮机低压缸排汽在不同气流角及不同总压分布下的流场,以模型为对象进行了三维流场的数值模拟.结果表明:排汽缸入口较大的旋流角会恶化排汽缸性能,而总压沿径向变化梯度为负时则有利于改善排汽缸气动性能.基于这一结果提出了通过改变总压分布抑制由于来流方向对排汽缸性能产生的负面影响的方法. 相似文献
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汽轮机运行条件存在随机波动性,对汽轮机的稳定运行造成一定影响。以往的研究多将汽轮机的工作环境条件作为确定因素,未考虑其随机变化的影响。本文将汽轮机背压、径向气流角和进口流量作为服从一定概率分布的随机变量,采用多项式混沌方法结合计算流体力学(CFD)模拟仿真,研究了以上参数的随机波动对某汽轮机末两级叶片气动性能的影响。结果表明:计算进口边界条件的设置方法对汽轮机末两级总体性能的计算结果影响不大,当给定进口流量边界条件时,末两级效率的计算结果最高;在接近堵塞工况时,进出口条件的随机变化对通流流量的影响不大,但效率存在明显的波动,进口气流角对总体性能的影响相对较小;当背压和进口流量存在随机波动时,末级动叶中激波位置小范围波动,激波位置对径向气流角的波动不敏感。 相似文献
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The complex 3D flow in a steam turbine exhaust hood model with different inlet swirl and inlet total pressure radial distributions has been simulated by employing CFX-5 and analyzed in this paper. It's found that the inlet tangential flow angle at hub has a negative effect on the exhaust hood performance, while a negative gradient of inlet total pressure radial distribution has a positive impact on the hood performances. It's also numerically con- firmed that a proper distribution of total pressure at hood inlet can successfully eliminate the negative effects caused by the inappropriate inlet swirl distribution and improve the hood aerodynamic performance. 相似文献
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To study the feasibility of using machine learning technology to solve the forward problem(prediction of aerodynamic parameters)and the inverse problem(prediction of geometric parameters)of turbine blades,this paper built a forward problem model based on backpropagation artificial neural networks(BP-ANNs)and an inverse problem model based on radial basis function artificial neural networks(RBF-ANNs).The S2(a stream surface obtained by extending a radial curve in turbo blades)calculation program was used to generate the dataset for single-stage turbo blades,and the back propagation algorithm was used to train the model.The parameters of five blade sections in a single-stage turbine were selected as inputs of the forward problem model,including stagger angle,inlet geometric angle,outlet geometric angle,wedge angle of leading edge pressure side,wedge angle of leading edge suction side,wedge angle of trailing edge,rear bending angle,and leading edge diameter.The outputs are efficiency,power,mass flow,relative exit Mach number,absolute exit Mach number,relative exit flow angle,absolute exit flow angle and reaction degree,which are eight aerodynamic parameters.The inputs and outputs of the inverse problem model are the opposite of that of the forward problem model.The models can accurately predict the aerodynamic parameters and geometric parameters,and the mean square errors(MSEs)of the forward problem test set and the inverse problem test set are 0.001 and 0.00035,respectively.This study shows that machine learning technology based on neural networks can be flexibly applied to the design of forward and inverse problems of turbine blades,and the models built by this method have practical application value in regression prediction problems. 相似文献
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To improve the aerodynamic performance of small axial flow fan, in this paper the design of a small axial flow fan with splitter blades is studied. The RNG k-ε turbulence model and SIMPLE algorithm were applied to the steady simulation calculation of the flow field, and its result was used as the initial field of the large eddy simulation to calculate the unsteady pressure field. The FW-H noise model was adopted to predict aerodynamic noise in the six monitoring points. Fast Fourier transform algorithm was applied to process the pressure signal. Experiment of noise testing was done to further investigate the aerodynamic noise of fans. And then the results obtained from the numerical simulation and experiment were described and analyzed. The results show that the static characteristics of small axial fan with splitter blades are similar with the prototype fan, and the static characteristics are improved within a certain range of flux. The power spectral density at the six monitoring points of small axial flow fan with splitter blades have decreased to some extent. The experimental results show sound pressure level of new fan has reduced in most frequency bands by comparing with prototype fan. The research results will provide a proof for parameter optimization and noise prediction of small axial flow fans with high performance. 相似文献
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炉膛中间截面边界条件对双切圆锅炉空气动力场计算的影响 总被引:1,自引:1,他引:0
大容量超超临界锅炉广泛采用单炉膛双切圆的空气动力组织方式,在计算流体力学软件FLUENT平台上,针对1GW超超临界单炉膛双切圆锅炉,计算了全炉膛和炉膛中间截面边界条件设为对称面和边壁条件的炉内空气动力场。计算表明,与标准κ-ε双方程模型相比雷诺应力模型(RSM)具有更高的计算精度;中间截面采用对称边界条件时,其流场分布规律与全炉膛模拟结果相似;中间截面为边壁条件时炉膛中间截面附近流速降低,但对整个炉膛流场影响较小;中间截面采用这两种边界条件均会导致1#、6#角射流衰减缓慢而冲刷炉膛前墙中间水冷壁。 相似文献