不同形状吸力面翼刀对叶栅二次流及性能的影响

本文以高负荷扩压平面叶栅为研究对象,基于雷诺时均方法进行定常数值计算,探讨吸力面翼刀侧面形状对吸力面二次流结构及气动性能的影响.吸力面翼刀位于25％叶高、33.3％～100％叶片弦长处,侧面形状分别为圆弧形以及倒圆角后的三角形和长方形,与叶片连接处采用融合过渡设计.在-3°,0°和3°三个工况下的分析结果表明:侧面形状...     

压气机叶栅壁面拓扑和二次流结构分析

本文从涡动力学原理出发，根据实验测量和流场显示结果，对压气机平面叶机的壁面拓扑和叶栅二次流结构进行了研究．由叶栅壁面拓扑分析和二次流结构可知，叶栅的通道涡较强，出口集中脱落涡和角区分离泡的存在，造成了叶栅两端区较高的二次流损失，并且随叶栅来流冲角的提高，旋涡出现破裂，二次流损失进一步提高．     

环形叶栅中二次流与损失的数值模拟

1引言三维叶栅中的损失主要由叶型损失、端部损失及二次流损失等组成。而其中的二次流损失,由于在损失总量中往往占有很大的比重,且又强烈依赖于叶栅几何形状等本身的特点,因而十分受到关注。许多学者分别用计算或试验的方法来研究二次流动,已经做了大量的工作（如文献1～8）。然而,以往大部分的研究往往局限于直列叶栅,对沿径向非等截面的环形叶棚的详细研究甚少。本文基于非正交曲线坐标与非正交速度分量下完全守恒型的Navier－Stokes方程,采用时间推进法与Baldwin－Lomax湍流模型,数值求解环形叶栅内部的粘性流场,得到了十分…     

采用端壁边界层抽吸方法抑制时栅二次流的效果分析

１前言叶栅端壁边界层和叶片表面边界层的发展及其产生的各种旋涡和分离流动对二次流损失有着重要的影响［１,２］,采用端壁边界层抽吸可以控制叶栅端壁上边界层的发展,从而降低二次流损失并改善出口气流的均匀性。同时,在汽轮机湿蒸汽静叶栅中有时也需在端壁上开设抽...     

环形压气机叶栅内部分离流结构分析 第一部分:近壁区分离流

1前言随着对叶轮机械研究的深入,叶轮机械内部的真实复杂流动已成为重要的研究课题。认识扩压叶栅内的流动分离和旋涡的发生、发展及相互作用,对于揭示压气机内部流动机制,改善流动结构,提高其喘振裕度,以及发展喘振控制技术都具有重要意义山。尽管人们已进行了许多研究,但尚未完整充分地认识这一复杂现象的物理现象和物理模型。对处在严重流动分离状态下的环形叶栅内部流动的研究就更为少见。本文应用油膜法显示了从约零度到二十几度多个来流攻角下,一大展弦比叶片低稠度环形压气机叶棚的表面流场。进口气流马赫数约为0．1。叶片进…     

不同负冲角工况下透平叶栅二次流的数值模拟及分析

本文应用TVD格式和Baldwin－Lomax代数紊流模型求解三维NS方程，对一个透平直列叶栅流场在两个不同的负冲角工况下进行了数值模拟，给出了叶栅马蹄涡及其分离鞍点、通道涡、角涡等二次流涡系的结构及其产生发展过程，并对不同工况下的涡系结构及冲角的影响作了详细的分析和比较．本文结果有助于对叶栅二次流涡系结构的产生发展机制的深入了解，同时表明所用数值求解技术有较高的精度和分辨率。     

弯曲时片压气机时栅内二次流的数值研究

本文应用Ｂｅａｍ－Ｗａｒｍｉｎｇ近似隐式因子分解格式以及ＭＭＬ代数湍流模型,采用拟压缩性方法求解雷诺平均拟压缩Ｎ－Ｓ方程组,对弯曲叶片压气机叶栅内的三维粘性流场进行了数值研究．结果表明,正弯曲叶栅内通道涡较直叶栅强,其诱导产生的壁面涡较弱且位于吸力面与壁端的角区内,与壁角涡接近．在正弯曲叶栅出口处,通道涡开始处于破裂前期,叶栅总损失增加。反弯曲叶栅通道涡较弱,其诱导的壁面涡很强,位于通道涡左上方,壁面涡和通道涡的有利作用,使通道涡更稳定,叶栅总损失比直叶栅和正弯曲叶栅要小．     

燃气透平叶栅端壁传热特性的数值研究

采用三维数值求解方法,对透平叶栅端壁区域的流动和传热特性进行了研究.利用试验数据考核了相应的数值方法,分析了网格数目和湍流模型对叶栅端壁附近流动传热特性计算的影响,比较了不同进口雷诺数和湍流度条件下端壁传热特性的变化。结果表明;马蹄涡和通道涡等二次流动直接影响端壁区传热,传热强度分布规律基本与当地流动的湍动能保持一致。湍流模型对端壁压力场的计算影响较小,但对端壁传热特性的求解的精度影响较大。采用v~3—f湍流模型能较好地预测端壁传热分布。来流雷诺数和湍流度的变化改变了端壁边界层厚度和涡系结构,使得端壁传热强度和梯度分布发生变化。     

端壁翼刀降低叶栅损失机理的实验研究

通过实验研究和拓扑分析的方法,分析了安装端壁翼刀后的压气机叶栅内流场的旋涡结构和演化过程.结果表明,安装翼刀后,在翼刀的安装位置产生了一对方向相反的旋涡,通道涡的强度减弱;马蹄涡的吸力面分支与叶栅吸力面相交的位置向下游推移,沿叶高向叶片中部流动的范围缩短,进而叶栅吸力面壁角区的流动得到了改善,降低了叶栅总损失.     

在大径高比环形透平叶栅中叶片弯曲对二次流影响的实验研究

1实验装置与模型叶片倾斜和弯曲的概念是针对小径高比环形叶栅提出来的。在短叶片环形叶栅中采用弯曲叶片的效果如何，本文作者对此进行了研究。同时也讨论了边界条件对静叶出口流场的影响。本实验是在哈尔滨工业大学的环形叶栅风洞上进行的。实验用的三套叶栅为：（1）常规径向叶片；（2）两端倾斜角为15”的弯曲叶片；（3）两端倾斜角为22“的弯曲叶片。其特性参数为：径高比为10．553，弦长b—31．Zmm，叶型安装角风一45．3“，进气角。0—90”，几何平均出气角。1—15”。出口马赫数M＝0．26左右。（1）（）（3）均为等截面叶栅，（2）…     

端壁凹槽控制扩压叶栅角区分离的数值研究

为揭示端壁凹槽控制高速扩压叶栅角区分离、降低叶栅气动损失的物理机制,采用数值方法研究了高速扩压叶栅NACA65-K48附加具有不同轴向位置和横向长度的端壁凹槽时叶栅的流场结构和气动特性.结果 表明:叶栅出口总压损失系数最大降低8.08％,静压升约提高0.67％.近端壁气流在凹槽内部诱导出复杂旋涡结构,该旋涡结构反过来为...     

等离子体对大折转角扩压叶栅性能的影响研究

探讨了等离子体影响扩压叶栅性能的机理,提出了一种考虑等离子体能量注入、可较全面评价等离子体改善叶栅流动所带来收益的损失评价方法。研究表明,等离子体可有效控制栅内流动分离、减小尾迹掺混,30kV电压下叶栅总压及能量损失分别减小12．3％和9．6％,同时等离子体也增加了壁面附近摩擦损失,分离区前施加流动控制时其效果变弱;等...     

跨音压气机转子近失速工况叶尖非定常流动分析

对跨音压气机Rotor35进行单通道全三维定常/非定常数值模拟,并与试验总性能和流场分布对比校核了数值计算精度。以此为基础开展的近失速工况点的非定常计算发现,来自相邻叶片通道未形成泄漏涡的间隙泄漏流体与来流、激波与泄漏涡干涉形成的低能破碎区相互作用形成了叶尖二次涡。叶尖二次涡向下游运动过程中,其所处的位置和产生的阻塞影响了近叶顶载荷的分布,最终使得叶尖部流场出现了循环往复的自维持的非定常波动现象。     

带根部间隙压气机静叶流道流动结构研究

本文采用数值模拟的方法对某低速压气机静叶流道内的流动结构进行了研究。设计工况下,带根部间隙的静叶流道中主要存在三个大尺度旋涡结构,分别为上通道涡、刮削涡和集中脱落涡,这些涡系在生成和发展过程中相互作用,流道内总奇点数先增加后减小,但都严格遵循了流道奇点数拓扑法则。     

Combined Flow Control Strategy Investigation for Corner Separation and Mid-Span Boundary Layer Separation in a High-Turning Compressor Cascade

To comprehensively control the corner separation and mid-span boundary layer (BL) separation, this study proposed and evaluated two new flow control configurations. One is a slotted configuration composed of blade-end and whole-span slots, and the other is a combined configuration with end-wall BL suction and whole-span slot. Additionally, the adaptability of the combined configuration to the lower blade solidity (c/t) condition was verified. The results indicate that both the slotted configuration and combined configuration can eliminate the mid-span BL separation, but a better reduction in the corner separation can be observed in the combined configuration. The two configurations can remove the concentrated shedding vortex and reduce the passage vortex (PV) for the datum cascade, but the wall vortex (WV) will be generated. By contrast, the combined configuration has weaker WV and PV than the slotted configuration, which contributes to further reducing the corner separation. In the combined configuration with a c/t of 1.66 and 1.36, the total pressure loss is reduced by 38.4% and 42.1%, respectively, on average, while the averaged static pressure rise coefficient is increased by 16.2% and 17.6%, respectively. This is advantageous for enhancing the working stability and pressure diffusion capacity for compressors. Besides this, the combined configuration with lower c/t can achieve a stronger pressure diffusion capacity and smaller loss than the higher c/t datum cascade. Therefore, the combined configuration is advantageous to the improvement of the aero-engine thrust-to-weight ratio through decreasing the compressor single-stage blade number.     

单级跨声速压气机旋转失速模拟方法

为了研究多排跨声轴流压气机旋转失速先兆的表现形式与失速演化规律,基于自主研发的CFD软件AS-PAC,通过发展动态重叠网格技术,流量出口边界条件以及节流阀边界条件,对单级跨声速压气机NASA Stage 35由近失速状态到完全失速状态的过程进行了模拟.结果表明,发展的数值模拟方法能准确地模拟多排压气机的旋转失速发展过程...     

Experimental Investigation of the Effect of Purge Flow and Main Flow Interaction in a Low-Speed Turbine Cascade Passage

In order to protect the vulnerable turbine components from extreme high temperature, coolant flow is introduced from the compressor to the disk cavity, inevitably interacting with the main flow. This paper describes an experimental investigation of the interaction between the main flow and the purge flow in a low-speed turbine cascade with three purge flow rates, Cm = 0, Cm = 1%, and Cm = 2%. In order to study the effect of the interaction between the main flow and the purge flow on the secondary flows, a Rortex method developed by Liu Chaoquan is introduced to identify the vortex in the flow field. In the meantime, a method to calculate the mean entropy production rate based on the particle image velocimetry (PIV) result is adopted to investigate the flow loss. The PIV result indicates that the purge flow has a prominent impact on the flow field of the cascade passage, changing the velocity distribution that induces a local blockage area. The results of vortex identification show that the purge flow promotes the generation of the passage vortex near the suction side. In addition, the purge flow makes the passage vortex migrate to the tip wall direction, enlarging the region affected by the secondary flow. The mean entropy production (MEP) result shows that the flow loss is mainly caused by the passage vortex. The coincidence of the high-MEP region and the location of the passage vortex indicates that the purge flow increases the secondary flow loss by affecting the formation and the migration of the passage vortex.     

Optimization on Secondary Flow and Auxiliary Entrainment Inlets of an Ejector by Using Three-Dimensional Numerical Study

In this paper, by using three-dimensional numerical simulations, the optimization of the cross-sectional area and angle of the secondary flow inlet is first conducted. Then, to further improve the ejector performance, an auxiliary entrainment is proposed and the optimization of the relative position, cross-sectional area and angle of the auxiliary entrainment inlet is accordingly performed by using three-dimensional methods. The results show that: (1) the performance of the ejector with the secondary flow in a vertical direction to the primary flow is slightly better than that in a parallel direction to the primary flow; (2) the effect of the cross-sectional area of the secondary flow has a relatively evident influence on ER, but its effect becomes ignored when the inlet area increases to a certain value; (3) the relative position and axial width of the auxiliary entrainment inlet are important factors influencing ejector performance, and after the optimization of these two geometries, the ejector ER can be increased by 97.7%; and (4) the optimization of the auxiliary entrainment inlet has a substantial effect on the ejector performance as compared to that of the secondary flow inlet. The novelty of this study is that the effect of an auxiliary entrainment on the ejector’s performance is identified by using a three-dimensional numerical simulation for the first time.     

Experimental and Numerical Investigation on Effects of the Steam Ingestion on the Aerodynamic Stability of an Axial Compressor

In order to investigate the influence of steam ingestion on the aerodynamic stability of a two-stage low-speed axial-flow compressor, multiphase flow numerical simulation and experiment were carried out. The total pressure ratio and stall margin of the compressor was decreased under steam ingestion. When the compressor worked at 40% and 53% of the nominal speed, the stall margin decreased, respectively, by 1.5% and 6.3%. The ingested steam reduced the inlet Mach number and increased the thickness of the boundary layer on the suction surface of the blade. The low-speed region around the trailing edge of the blade was increased, and the flow separation region of the boundary layer on the suction surface of the blade was expanded; thus, the compressor was more likely to enter the stall state. The higher the rotational speed, the more significant the negative influence of steam ingestion on the compressor stall margin. The entropy and temperature of air were increased by steam. The heat transfer between steam and air was continuous in compressor passages. The entropy of the air in the later stage was higher than that in the first stage; consequently, the flow loss in the second stage was more serious. Under the combined action of steam ingestion and counter-rotating bulk swirl distortion, the compressor stability margin loss was more obvious. When the rotor speed was 40% and 53% of the nominal speed, the stall margin decreased by 6.3% and 12.64%, respectively.