计及前缘形状变化的离心式压气机流场分析

通过两种转速(120 000r/min和140 000r/min)下压气机性能试验与仿真结果对比分析得知其总体误差范围在5%左右,验证了ANSYS CFX软件在压气机性能模拟计算的可靠性;采用数值计算方法分别对具有圆形和椭圆形前缘的压气机叶轮与涡壳的组合性能进行计算,得到了相关转速下压气机特性曲线,分析了四种不同长短径之比(a/b=1、3、5、8)前缘的叶轮流道内的气体流动特性。研究结果表明:压气机特性随着前缘长短径比值的增大呈先增后减的趋势,最高压比LE5比LE1提高了5%,最大效率LE3比LE1提高了6.7%,且流量范围也有所增加;在一定范围内增大前缘长短径比可以抑制前缘分离流动,改善叶轮出口处流场。     

单级离心压气机气动性能预测与优化设计

为了提升低转速工况下压气机的气动性能,采用人工神经网络与遗传算法相结合的优化方法对某单级离心压气机离心叶轮的弯特性进行优化计算。利用NUMECA软件对该离心压气机进行了不同转速的数值模拟,得到压气机不同工况下的气动性能。通过设置不同控制参数和曲线形式对离心叶轮叶片进行参数化拟合,以8个改变叶片弯特性的参数为自由参数进行了叶型优化设计,最终得到了优化后的叶轮叶片。结果表明:优化后在低转速的设计工况下离心压气机压比增加了4.69%,稳定裕度拓宽了17.41%。     

涡轮增压器压气机蜗壳型线变化的性能研究

利用数值模拟的方法,研究蜗壳形状对涡轮增压器压气机性能的影响。根据蜗壳成型方法(C_ur~x=const,0≤x≤1),取不同的x经验数值(x=0、0.2、0.4、0.6、0.8、1),建立6个蜗壳模型分别与某叶轮的组合性能进行了计算。得到了设计转速下的流量与整机效率及压比的特性曲线并进行比较。分析了靠近设计工况点的叶轮、扩压器及蜗壳流道内的气体流动特性和压比分布。结果表明:在一定范围内x增大,能使流量增大,效率提高,抑制流动分离。本例中x取0.8时总体性能较优。     

高海拔条件下压气机结构优化及其对柴油机性能的影响

基于二级可调增压柴油机高海拔性能试验,采用计算流体力学(CFD)和柴油机工作过程计算方法,开展高海拔条件下压气机叶轮结构优化及其对柴油机性能影响的研究.研究结果表明:海拔5 500 m,压气机叶轮主叶片及分流叶片前缘前掠6.27°、分流叶片向主叶片压力面偏折12.09°,压气机叶轮流道内流动损失明显降低,出口处流动稳定性提高,压比、效率及流量范围分别提高4.16%、2.63%及6.58%;压气机叶轮优化后,二级可调增压柴油机中低转速燃烧过程得到明显改善,滞燃期和燃烧持续期缩短;柴油机1 200 r/min全负荷工况最高燃烧压力升高9.53%,累计放热量提高8.78%,转矩提高5.82%,燃油消耗率降低4.42%.     

分流叶片周向位置设计及其对离心叶轮内部流动的影响

利用计算流体力学软件,对某高压比、高转速、小流量离心式压气机的半开式叶轮内部三维粘性流场进行了数值模拟研究。重点分析了分流叶片周向位置对叶轮内部流动和性能的影响,提出了适合此半开式离心叶轮分流叶片周向位置的设计方案。结果表明：分流叶片不同周向位置对流场影响明显,当分流叶片偏向长叶片吸力面侧时,叶轮流道内低速区增大,流动分布不均匀。研究还发现：固定分流叶片进口而将出口位置向长叶片压力面侧偏置,可以改善叶轮内部流动情况,提高叶轮性能。     

一种流量范围甚宽的压气机的设计和试验

压气机叶轮内部流动的基本理论研究指出:a)解决压气机内部非粘性流动问题能获得防止喘振的必要(但不是充分的)准则;b)采用后倾叶片不是唯一可以增加压气机有用流量范围的叶片通道改进措施;c)能获得一个比原来想象宽得多的有用流量范围。本研究建议的一种可供选取的方法已在3. 0以上的压比下进行了试验。这种新方法在能使叶轮的设计转速下的喘振流量减少百分之五十时导风轮几何尺寸与作为比较标准的常规径向叶片叶轮的导风轮尺寸保持一致。这种方法提供了预测径流涡轮机械的喘振流动特性的可能性。反之,也可以由预先给定叶片几何尺寸来设计能满足预先规定的喘振堵塞流量比的元件。看来在不牺牲元件最大效率的情况下,离心压气机的有用流动范围能扩大到堵塞流动能力的15～20%。     

叶片前缘不同后掠角对离心压气机气动性能的影响

采用全三维气动设计技术,设计了4种具有掠角叶片和带翼型叶片扩压器的涡轮增压跨音速离心压气机,并采用数值模拟手段研究了叶片前缘不同后掠角对压气机内部工质流动的影响。研究结果表明:主叶片前缘不同后掠角会使压气机堵塞流量(堵塞工况下的工质流量)增加,提高压气机流通能力,同时,可以有效改善通道内低能流团的分布;但由于主叶片轴向弦长缩短,会造成喘振裕度的减少,以及主叶片前缘脱体激波角增大和槽道激波的增强;对截面二次流分析结果表明:叶片前缘的后掠角对二次流的影响主要表现在叶轮进口附近,对出口影响不大。对比不同前缘后掠角压气机内部流动情况发现,掠角越小,叶片叶顶负荷越小,叶片表面压差也越小,流动越稳定;掠角越大,虽然叶轮通道上游产生的激波越强烈,但是可以明显改善通道下游气流流动情况。     

几何参数变化对离心压气机性能影响的仿真研究

采用离心压气机性能仿真数学模型研究某些几何参数，如叶片顶部间隙，叶轮叶片出口角变化对压气机性能产生的影响，是当今设计高压比、宽工作范围、高效离心压气机的关键步骤。为此，首先建立了离心压气机性能仿真数学模型。为了验证数学模型的有效性，对Krain叶轮性能进行了计算。随后，对不同叶片顶部间隙，不同出口叶片角的压气机性能进行仿真研究。研究结果表明，随顶部间隙的增大，压气机效率及压比下降；后弯叶轮性能优于径向叶轮。     

柴油机高原适应性研究及压气机流场分析

基于试验测试数据建立增压柴油机的仿真模型,开展0～4 000m高原适应性研究工作,研究增压柴油机性能及压气机性能海拔变化关系,并研究不同海拔下压气机内部流动状况,分析压气机效率下降原因。研究结果表明:高海拔工况下,柴油机功率、转矩与燃油消耗率下降,进气流量减少,增压压力下降,压气机压比增大,效率下降。压气机子午面的相对总压的低压区域压力较小,叶顶间隙间及叶轮出口高熵值区域增大且范围提前。跨音速流动区域增大,激波损失增大,叶顶间隙流加强,泄漏损失增大,分流叶片压力侧主流与低速泄漏流掺混,尾迹区域增大,掺混损失增加,压气机叶轮内部损失增大。因此高原环境下,压气机效率降低。     

小流量离心压气机的设计与流场计算

介绍了一个带有分流叶片的小流量离心压气机的设计过程。这个叶轮的主要设计参数为流量0．215kg／s，转速95000r／min，压比1．8。简要介绍了离心压气机设计系统，其中包括初步设计及优化模块，性能仿真模块，叶轮造型模块。使用三维NS方程对所设计的离心压气机在设计点的性能进行了计算，计算结果表明所设计的离心压气机基本能够满足设计要求。     

Numerical simulation of novel axial impeller patterns to compress water vapor as refrigerant

Through means of 3-D CFD (Computational Fluid Dynamics) method, a novel axial compressor with different impeller shapes compressing water vapor as refrigerant was investigated. The numerical simulation focuses on the fluid flow from compressor impeller inlet to outlet. The overall performance level and range are predicted. Different blade patterns with different hub sizes were compared regarding the aerodynamic performance. Independent of the blade pattern, in this numerical investigation the largest hub diameter shows the highest pressure ratio and efficiency at narrowest operating range.     

Effect of blade wrap angle in hydraulic turbine with forward-curved blades

Hydraulic turbine is used for recovering power by using reverse running pump. In order to improve the efficiency of turbine working condition, the impeller with forward-curved blades was applied instead of the impeller with backward-curved blades. The effects on the performance of hydraulic turbine and inner flow character with different blade wrap angles were studied by the method of numerical simulation. The results show that: with the blade wrap angle growth, the maximum efficiency increases, but the range of the flow rate at the high efficiency decreases rapidly; the flow state of hydraulic turbine which in small flow area obtains a remarkable improvement; the flow within the impeller improves and the friction loss increases; the hydraulic loss in the small flow area inside the impeller declines but it grows in the large flow area.     

Influence of blade outlet angle on performance of low-specific-speed centrifugal pump

In order to analyze the influence of blade outlet angle on inner flow field and performance of low-specific-speed centrifugal pump, the flow field in the pump with different blade outlet angles 32.5° and 39° was numerically calculated. The external performance experiment was also carried out on the pump. Based on SIMPLEC algorithm, time-average N-S equation and the rectified k-? turbulent model were adopted during the process of computation. The distributions of velocity and pressure in pumps with different blade outlet angles were obtained by calculation. The numerical results show that backflow areas exist in the two impellers, while the inner flow has a little improvement in the impeller with larger blade outlet angle. Blade outlet angle has a certain influence on the static pressure near the long-blade leading edge and tongue, but it has little influence on the distribution of static pressure in the passages of impeller. The experiment results show that the low-specific-speed centrifugal pump with larger blade outlet angle has better hydraulic performance.     

基于内部流场分析的离心风机改型设计

本文以某型离心风机为基础,依靠数值模拟的方法,基于对风机内部流场的分析,对其进行优化改型设计。主要分为三个方面：其一,将叶轮的直叶片改型为前掠正弯叶片,控制端区低能流体堆积,抑止叶栅流道分离流动的发生;其二,根据弯掠优化得到的叶轮设计改型风机机壳,以适应弯掠叶轮的出口气动条件;并根据弯掠叶轮与改型机壳内部流动的分析,对叶轮采取根切的优化方法,保持风机全压和流量在合理的大小。得到的优化设计风机,在保持全压和流量基本与原型相等的条件下,效率提高5%以上。     

叶片根部倒角对离心叶轮气动性能影响

叶轮是决定离心压气机气动性能的关键因素之一,在保持叶轮设计参数不变的条件下,调整叶根倒角的分布,对比分析叶根倒角对压气机性能的影响.利用Numeca软件对跨声速离心压气机进行全三维稳态流动数值模拟方案分为等半径倒角与变半径倒角两种.结果表明:主叶片后半弦长的倒角是决定压气机气动性能的关键性因素,尾缘倒角比前缘更敏感;根...     

基于弯曲叶片的氦气轴流压气机优化设计

针对高负荷氦气压气机中角区分离、叶顶泄漏严重带来的效率损失问题,以单级氦气压缩机为研究对象,利用CFD方法,分析了不同弯曲角度下氦气压气机内部的角区损失和叶顶泄漏损失,并优化了现有五级轴流氦气压气机。结果表明：叶片正弯会增加端区处的静压,减少角区分离,进而降低角区损失;对动叶而言,在设计攻角下正弯也会增加前缘损失;动叶叶顶反弯使泄漏流远离下一个叶片的压力面,而合适的反弯角度可以降低叶顶泄漏量;选取合适的弯曲角度使五级轴流压气机设计点效率提高1.85%。     

Study of unsteady flow simulation of backward impeller with non-uniform casing

The flow characteristics of the centrifugal fans with different blade outlet angles are basically discussed on steady and unsteady simulations for a rectangular casing fan. The blade outlet angles of the impellers are 35° and 25° respectively. The unsteady flow behavior in the passage of the impeller 35° is quite different from that in the steady flow behavior. The large flow separation occurs in the steady flow field and unsteady flow field of the impeller 35°, the flow distribution in the circumferential direction varies remarkably and the flow separation on the blade occurs only at the back region of the fan; but the steady flow behavior in the impeller 25° is almost consistent with the unsteady flow behavior, the flow distribution of the circumferential direction doesn't vary much and the flow separation on the blade hardly occurs. When the circumferential variation of the flow in the impeller is large, the steady flow simulation is not coincident to the unsteady flow simulation.     

Optimal ratio of bend channel in centrifugal compressor

A numerical investigation on the flow in a bend channel by coupling the impeller with the vaneless diffuser in a centrifugal compressor with different r/b ratios (bend radius r to bend channel width b) is presented. The jet-wake effect of the impeller outlet is considered and flow pattern in the bend channel and the performance of the centrifugal compressor stage are investigated. The results indicate that there is an optimal r/b ratio for increasing the stage efficiency to the highest for a specific compressor stage. The change in r/b ratio significantly affects the flow angle of the bend channel outlet. The prime reason for the total pressure loss in the bend channel is the wall friction in the bend channel.