不同吞雨形式下压气机特性数值模拟

为研究不同吞雨条件下雨滴的运动形式以及各级压气机的性能变化特点,以某三级压气机为研究对象,使用CFX软件进行数值模拟,选择k-ε湍流模型,针对压气机干压缩、整周均匀吞雨和周向非均匀吞雨3种不同工况,对比分析雨水对压气机流场和性能的影响机理。结果表明：雨滴和空气之间的粘性力引起的额外流动损失以及雨滴的蒸发效果在各级压气机内存在差异,雨水在进口局部区域浓度较大将导致流场沿周向分布不均匀;相比于均匀吞雨,多级压气机非均匀吞雨工况下整机性能下降幅度增大,稳定工作范围进一步减小;雨滴的蒸发强度沿流动方向逐渐增大,因此前两级工作特性变化情况与整机较为一致,而第3级在部分工况点的效率略有升高。     

转速对跨声速轴流压气机的性能影响分析

为了研究跨声速压气机内部流动失稳对压气机性能的影响,对跨声速轴流压气机NASA转子37进行三维定常数值模拟,研究不同设计转速下跨声速轴流压气机稳定运行及内部流动失稳现象。研究发现：转速不变时近堵塞点的等熵效率高于近失速点;随着转速降低,压气机稳定运行范围变宽、效率增大及流动损失变小;压气机叶栅通道出现堵塞情况的叶高截面范围随着转速的降低而逐渐增大,这导致压气机叶片在近失速点处的流动失稳情况变严重。     

多级轴流压气机模化设计中尺寸缩放对气动性能影响的数值研究

为了研究几何尺寸模化缩放及叶尖间隙对多级轴流压气机气动性能及内部流动的影响,采用Numeca程序对17级轴流压气机开展了数值计算。结果表明：在80%及100%等高转速条件下压气机效率随着模化比例增大而增大,而在50%转速下模化缩放对压气机效率的影响较小。相对于原型压气机,模化放大时,压气机前8级单级压比均有所降低,而后8级压比均提高;模化缩小时,压气机的变化规律则相反。随着压气机几何尺寸的增大,静叶叶根和叶尖区域的总压恢复系数显著提高。同时,叶片叶尖泄漏流区域的熵增减少,从而使各级效率均有所提升。缩放模化中,随着叶尖间隙的增大,泄漏流增多,恶化了动叶叶尖附近的流动分离,降低了动叶后50%弦长区域的相对马赫数,同时扩大了静叶上端壁的流动分离,使压气机效率降低。     

展弦比对船用燃气轮机低压压气机跨音级性能影响研究

为了揭示展弦比对压气机跨声速级气动性能的影响机理,进一步提高舰船燃气轮机低压压气机的气动性能,采用数值模拟方法研究了展弦比对某船用燃气轮机低压压气机跨声速级气动性能的影响.结果表明:展弦比对压气机性能的影响受到扭曲规律和反动度等参数选择的影响,对于不同的扭曲方式和反动度分别存在着效率最优展弦比和喘振裕度最优展弦比,且在...     

进口参数变化对高压压气机性能影响研究

以某型高压九级轴流压气机为研究对象,利用NUMECA软件在不同进口条件下进行变工况性能模拟计算。研究了变转速下由于进口总温、总压的改变引起的雷诺数变化对压气机性能影响。结果表明:试验条件与设计条件下的试验结果相比,进口雷诺数由1.348×10~6下降到4.318×10~5,压气机设计点折合流量比减小0.008,效率下降0.72%,喘振裕度降低了8.11%,压气机性能曲线整体向左下方移动;在一定范围内升高进口总压或降低进口总温,将改善压气机的压比、效率以及折合流量比;当雷诺数高于一定临界值后,同一转速下的压气机的效率以及折合流量比基本保持不变;当转速降低至设计转速以下时,临界雷诺数将进一步增大,雷诺数效应影响增强;雷诺数降低会导致泄漏流损失增大,径向涡损失增强,加剧叶尖区域的流动分离,此时叶尖区域的流动阻塞成为引起流动失稳与整机性能恶化的主要原因。     

颗粒沉积和冲蚀损伤对轴流压气机性能影响的研究进展

针对微细颗粒沉积与冲蚀损伤会造成压气机性能退化甚至设备失效的问题,系统总结了近年来国内外研究机构在颗粒沉积与冲蚀损伤对压气机性能影响方面的研究进展,重点介绍了颗粒沉积和冲蚀损伤造成的压气机性能退化机制、压气机性能退化特性数值模拟方法和实验研究方法以及典型研究成果等。基于当前研究热点和发展趋势,提出了颗粒沉积和冲蚀损伤对轴流压气机性能影响研究下一步应重点开展的方向,即借助于精细化数值模拟及可视化实验技术探索轴流压气机流道非定常流场细节与微细颗粒运动行为之间的相互作用机制,揭示颗粒沉积与冲蚀损伤导致的压气机性能退化机理,建立颗粒沉积、冲蚀损伤与压气机性能退化的定量关系。     

封严篦齿对轴流压气机涡系结构与流动损失的影响

为了解决压气机级间泄漏与二次流流动问题,航空发动机轴流压气机静叶根部与转子之间通常采用篦齿进行封严。为研究封严篦齿泄漏流对压气机性能的影响,基于某轴流压气机建立了带封严篦齿真实结构的几何模型,采用三维数值模拟的方法,研究了篦齿泄漏流对某轴流压气机主流涡系结构和流动损失的影响,并探究了其影响机理。结果表明：封严篦齿泄漏流使压气机的压比和效率都有不同程度的下降;篦齿泄漏会增强上游转子叶根吸力面的尾缘角区涡和静子叶根吸力面的马蹄涡,并使设计工况的上游转子和静子的流动损失分别增大3.1%和13.1%;静子叶根后附面层低能流体被抽吸,改善了下游流场,使下游转子流动损失减小2.4%;在近喘振点,由于压气机内流场恶化严重,篦齿泄漏带来的流场变化并不显著,泄漏流对主流影响小。     

畸变强度对压气机气动性能影响研究

以Stage 35为研究对象,采用商业软件ANSYS CFX开展进气总压畸变对压气机性能影响的数值模拟研究。在70%叶高处安装插板式畸变模拟器,改变插板位置,得到3种不同畸变度的进气总压畸变。计算结果表明:当插板与动叶的距离分别为42,32和22 cm时,压气机压比分别下降了3.45%、3.66%和4.51%;效率则依次降低了5.10%、5.12%和6.95%;稳定裕度降低了25%、26.11%和26.62%。总压畸变会显著影响压气机内部流动,改变动叶进气角,导致动叶尾缘分离区域增大,尾迹损失增大;进口总压畸变度越大,压气机总压比下降越多,整机绝热效率越低,稳定工作裕度越小。     

船用燃气轮机低压压气机气动布局规律研究

为缩短燃气轮机低压压气机的设计周期,获取一维设计中各关键设计参数分布规律,同时得到最优的一维设计参数选取方案,采用基于HARIKA算法的压气机一维设计与分析程序对某型船用低压压气机流量系数、载荷系数和反动度的轴向布局方法进行了研究并提炼了各参数分布的数学模型。其中,流量系数和载荷系数沿级分布为近似单峰值的三次多项式曲线,反动度分布为"二段式",通过改变流量系数和载荷系数的峰值点坐标和改变特定级反动度和反动度变化步长的方法,研究了不同布局方式对效率、喘振裕度以及压比的影响,最后结合优化算法得到了最优参数分布方案。结果发现:流量系数峰值位置在第6级,载荷系数在第5级或第6级时效率和喘振裕度性能较好;第四级反动度取值0.5～0.52时效率较高;相比载荷系数和反动度,流量系数对非设计工况性能影响更为显著,优化后的参数分布方案在各转速下喘振裕度均有所提高。     

进气畸变度及分布形式对跨音速轴流压气机工作特性的影响

为了研究进气畸变对压气机的工作特性以及稳定性的影响,以NASA Stage35型跨音速轴流压气机为研究对象,采用全通道计算模型对不同畸变程度和不同畸变分布形式条件下压气机的工作特性及内部流场变化规律进行数值模拟研究。结果表明:随着进气畸变度的不断增加,压气机的峰值效率逐渐下降,由畸变所引起的总压损失在压气机内部流道中逐渐扩大;在保持畸变度和畸变区域总面积不变的条件下,畸变区的分散程度对压气机在峰值效率点附近的工作特性影响较小,但随着畸变分布区分散程度的逐渐增加,压气机的稳定裕度有所提高,压气机内部流道中的总压损失和熵增也有所降低。     

Unsteady performance and thermodynamic analysis of aero-engine compressor at different water ingestion conditions

Aero-engine compressor is seriously threatened by the ingestion of liquid water. This article aims to deeply study the influences of different water contents and droplet diameters on the unsteady performance and thermodynamic parameters of compressor through frequency spectrum analysis. The accuracy of numerical calculation for compressor performance is verified by experimental data. Results show that the compression performance will be reduced and the unsteady fluctuations inside compressor will be aggravated after water ingestion. For some important parameters, such as mass flow rate, total pressure and temperature ratio, as well as efficiency, their main frequencies are changed from the original blade passing frequency to the rotor passing frequency (RPF), and their amplitudes are also significantly amplified. The working point of compressor will experience the nonoptimal state with large amplitude and period for a long time, which is not conducive to the stable operation of the compressor. Moreover, within the range of 2% to 8% water contents and 50 to 150 μm droplet diameters, the fluctuation amplitude is correspondingly exacerbated with the increase of water content or droplet size, but its main frequency is maintained at RPF. Particularly, the tip clearance is the most sensitive region affected by water ingestion where the fluctuations of static pressure and temperature are the largest. The point that water content has a greater influence on the performance fluctuation of compressor is also confirmed in this article.     

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%。     

压气机动叶CLOCKING效应对叶片可靠性影响的数值研究

采用基于谐函数(harmonic)的非定常计算方法,数值模拟了某型燃气轮机中间三级轴流压气机流场,研究第二级动叶CLOCKING效应对中间级静叶片气动负荷的影响。通过对各列叶片非定常气动力和气动力矩进行时域分析,指出不同CLOCKING位置对应的气流激振力对叶片的气动负荷造成了明显的影响。进行了中间级动叶和静叶的振动可靠性分析。计算结果表明,该压气机的3组静叶片避开共振区的程度各不相同。R2转子叶片处于不同的CLOCKING位置会引起下游S2静叶片气流激振力发生显著变化,导致S2叶片产生比较强烈的共振。     

跨声速串列转子叶型流动特性分析

串列叶片技术可以突破常规压气机叶片的负荷极限,因此成为下一代高负荷压气机设计技术的研究热点。为了拓展串列叶片的使用范围,采用数值模拟的方法对跨声速串列转子叶型（来流马赫数1.2）流动特性及前排叶片尾迹发展演化规律展开研究。得出结论：全工况范围内,前排叶片总压损失占比超过50%,前排叶片激波系结构的优化设计是影响串列叶型性能的关键因素;随着出口背压提高,前排叶片尾迹厚度先增加后减小,导致尾迹厚度不同的根本原因是流出前排叶片通道时尾迹的初始速度亏损不同,后排叶片通道的扩压对初始速度亏损有进一步的放大作用。     

轴流压气机叶片磨损位置模拟方法研究

采用气固两相流计算方法,对某型燃气轮机压气机实际工作环境中沙尘颗粒对压气机叶片磨损特性进行了全三维数值模拟研究,分析了叶片表面磨损位置的分布情况。研究表明：同级与不同级压气机叶片均呈现出明显的非均匀磨损特性,同级叶片的最大磨损浓度可以达到最小磨损浓度的2.9倍,不同级叶片的平均磨损浓度最大相差17.8倍;同一叶片上,颗粒对叶片前缘的磨损程度高于尾缘;随着转速的增大叶片的磨损率最大增加120%且非均匀性进一步增强。     

Numerical Investigation of the Superimposed Effects on Stator Wake Oscillation in an Axial-radial Combined Compressor ZHAO Ben,YANG Ce,HU Liangjun,ZHOU Mi and ZHANG Jizhong简

The superimposed influences of the blade rows in a multistage compressor are important because different matches of upstream and downstream blades can result in significant differences in the stator wake oscillation. Numerical inves- tigation of the axial stator wake oscillation, which is affected upstream by the axial rotor and downstream by the radial rotor, was performed in an axial-radial combined compressor. Many configurations with different blade numbers and locations, which influence axial stator wake oscillation were investigated. When rotors have equal blade numbers, the axial stator wake oscillates periodically versus time within time T （moving blade passing 1/3 revolution）. In contrast, stator wake oscillates irregularly within T when rotors have different blade numbers. A model-split subtraction method is presented in order to separate the influences of the individual blade rows on the wake oscillation of the axial stator. Analysis from the rotor-stator configuration showed that the unsteady flow angle fluctuation response is caused by the upstream rotor. For the rotor-stator-rotor configuration, the unsteady flow angle fluctuations are influenced by up- and downstream blade rows. With the model-split subtraction method, the up- and downstream influences on the flow angle fluctuation could be clearly separated and quantified. Low amplitudes could be observed when the influences from up- and downstream moving rows were superimposed with the ＂positive peak- negative peak＂ type wave. Clocking investi- gations were carried out to change the relative superimposed phase of influences from the surrounding blade rows in or- der to modulate the amplitudes of the axial stator wake oscillation. However, the amplitudes did not reach the maximum when they were superimposed with ＂positive peak-positive peak＂ type wave due to the impact of the interaction between the two moving blade rows.     

Kinetic energy extraction of a tidal stream turbine and its sensitivity to structural stiffness attenuation

The hydrodynamic forces imparted on a tidal turbine rotor, whilst causing it to rotate and hence generate power, will also cause the blades to deform. This deformation will affect the turbine's performance if not included in the early design phase and could lead to a decrease in power output and a reduction in operational life. Conversely, designing blades to allow them to deform slightly may reduce localised stress and therefore prolong the life of the blades and allow the blades to deform in to their optimum operational state. The aim of this paper is to better understand the kinetic energy extraction by varying the material modulus of a turbine blade. Shaft torque/power, blade tip displacement, and axial thrust results are presented for 2, 3 and 4 bladed rotor configurations at peak power extraction. For the rotor design studied the FSI model data show that there is a low sensitivity to blade deformation for the 2, 3 and 4 bladed rotors. However, the results reveal that the 3 bladed rotor displayed maximum hydrodynamic performance as a rigid structure which then decreased as the blade deformed. The 2 and 4 bladed rotor configurations elucidated a slight increase in hydrodynamic performance with deflection.     

Stall characteristics and tip clearance effects in forward swept axial compressor rotors

Tilting the blade sections to the flow direction (blade sweep) would increase the operating range of an axial compressor due to modifications in the pressure and velocity fields on the suction surface. On the other hand, blade tip gap, though finite, has great influence on the performance of a turbomachine. The present paper investigates the combined effect of these two factors on various flow characteristics in a low speed axial flow compressor. For this present study, nine computational domains were modeled; three rotor sweep configurations (0°, 20° and 30°) and for three different clearance levels for each rotor. Commercial CFD solver ANSYS CFX 11.0 is used for the simulations. Results indicated that tip chordline sweep is found to improve the stall margin of the compressor by modifying the suction surface boundary layer migration phenomenon. Diffusion Factor (DF) contours showed the severity of stalling with unswept rotor. For the swept rotors, the zones of high probable stall are less severe and they become less in size with increasing sweep. Increment in the tip gap is found to gradually affect the performance of unswept rotor, while the effect is very high for the two swept rotors for the earlier increments. As a minimum clearance is unavoidable, swept rotors suffer relatively higher deviation from the idealistic behavior than the unswept rotor due to tip clearance.     

基于叶片弯掠技术的优化设计

在三维粘性流场的数值计算程序平台上,利用BP神经网络和遗传算法,通过叶片弯掠技术对一轴流风机的转子叶片的周向弯曲角度进行寻优,以使风扇的气动性能进一步提高。通过对比优化前、后的叶轮发现,优化之后的叶片呈现明显的周向前弯曲特征。测试结果显示,其全压和气动效率分别提高了3.56%和1.27%,失速裕度大幅度拓宽36%以上,上、下端部的损失进一步降低。     

Influence of Hub Contouring on the Performance of a Transonic Axial Compressor Stage with Low Hub-Tip Ratio

The rotor blade height with low hub-tip ratio is relatively longer,and the aerodynamic parameters change drastically from hub to tip.Especially the organization of flow field at hub becomes more difficult.This paper takes a transonic 1.5-stage axial compressor with low hub-tip ratio as the research object.The influence of four types of rotor hub contouring on the performance of transonic rotor and stage is explored through numerical simulation.The three-dimensional numerical simulation results show that different hub contourings have obvious influence on the flow field of transonic compressor rotor and stage,thus affecting the compressor performance.The detailed comparison is conducted at the rotor peak efficiency point for each hub contouring.Compared with the linear hub contouring,the concave hub contouring can improve the flow capacity,improve the rotor working capacity,and increase the flow rate.The flow field near blade root and efficiency of transonic rotor is improved.The convex hub contouring will reduce the mass flow rate,pressure ratio and efficiency of the transonic rotor.Full consideration should be given to the influence of stator flow field by hub contouring.