共查询到19条相似文献,搜索用时 169 毫秒
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论述了时间相关有限差分法在跨音速叶栅流动计算中的应用,并以具有代表性的跨音速压气机叶栅流场的计算和图样的制取为例,附以程序编制及其流程图,详细地讲解了计算程序的具体操作。由比较可以看出此方法较以前的时间推进法要快得多。可以预期,随着该方法的不断完善,得到更为精确的结果是完全有可能的。 相似文献
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本文介绍了在我国首次利用气水模拟方法对某高负荷跨音速透平动、静叶栅进行详尽的空气动力学试验研究的结果,并将结果与平面叶栅风洞试验及叶栅绳流的计算结果进行比较。气水模拟方法对跨音速叶栅的方案设计和定性分析具有正确、直观、简便、经济的优点。本方法不仅可替代繁重的平面叶栅高速风洞的试验工作,还可验证跨音速叶栅绕流的计算结果。 相似文献
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本文综述了在设计透平跨音速叶栅时气流出气角的各种计算方法和相应的公式,并和试验结果进行了对比。文中还提供了收缩——扩张形流道的跨音速叶栅出气角计算时所用的曲线。 相似文献
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本文提出了一个计算跨音速透平叶栅的极限进气角的方法。该法以叶栅的相对极限环量为根据。用本法计算得到的极限进气角和实验结果吻合较好。 相似文献
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跨音速透平叶栅极限进气角的确定 总被引:1,自引:0,他引:1
本文提供了一个计算大功率汽轮机末级动叶顶部截面跨音速叶栅的极限进气角的方法.按本方法求得的极限进气角与吹风试验及数值试验的结果吻合较好. 相似文献
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本文叙述了在跨音速风洞中模拟跨音速透平叶片尾缘流动的试验结果.分析了跨音速透平叶片尾缘流动的机理.说明了诸如附面层、叶片尾缘厚度、来流马赫数等因素对尾缘死水区基压的影响.提出通过改变尾缘形状来改善跨音速叶栅气动特性的途径.图8表1参15 相似文献
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将一跨音速静叶栅数值计算结果与实验结果进行了比较,表明计算与实验结果吻合的较好.为了讨论跨音速压气机中弯掠叶片适用的展弦比条件,在0°攻角下,展弦比为1.25、1.50和2.00,对0~30°弯掠叶片流场进行了数值分析,结果表明,当10°弯掠角时,小展弦比弯掠叶片对叶片性能影响较为明显;而在20°弯掠角时,大展弦比弯掠叶片对叶片性能影响较为明显.弯掠叶片使前缘激波转化为斜激波,并减弱了通道激波的强度,因而降低了叶栅激波损失.可以证明,在跨音速条件下展弦比的大小是如何使用弯掠叶片的一个重要的参考因素. 相似文献
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为了探索在超跨音速下具有优良启动特性的叶型,以某跨音速叶型为例,对吸力面作了“凹”形设计,分析比较了改型前后叶栅气动性能的变化,为叶型设计提供一种思路。 相似文献
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为了探索在超跨音速下具有优良启动特性的叶型,以某跨音速叶型为例,初步尝试设计海豚叶型,并对其流场进行了数值模拟,以评估这种叶型是否适合于超跨音速流动。 相似文献
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INTRoDUCTIoNInmodernturbomachinery,withtheincreasingstageload,thetransoniccascadesbecomemorewidelyused,sothedesignofhighperformancetransoniccas-cadesisacriticaJpracticalproblem.Performanceop-timizationofaerodynamicshapeplaysanimportantroleinthedesigntasksofttirbomachinery,andisanactiveresearchfield.Awidevarietyoftechniqueshavebeendeve1opedtofacethisprobleml1].FuIthermethodsbasedonartificialintelligence-expertsystemtechniqueshavealsobeenintroducedl2].Butthediffusionofauto-matedshapedesigni… 相似文献
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针对跨声速压气机叶片内复杂的三维流动,采用自行开发的三维CFD程序对跨音速轴流压气机NASA Rotor 37流场进行数值模拟,对比分析了L-F(Lax Friedrichs)、Steger Warming及Van Leer 3种通矢量分裂格式和AUSMDV混合格式在跨声速叶轮流场数值计算时的格式效应。研究表明:与其他格式相比,AUSMDV在设计工况下的计算结果与实验误差最小,对激波和叶顶间隙泄漏的捕捉能力最强,Van Leer格式次之;Steger Warming格式在计算过程中收敛性最好。 相似文献
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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. 相似文献
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Naixing Chen Hongwu Zhang Yanji Xu Weiguang HuangInstitute of Engineering Thermophysics Chinese Academy of Sciences P.O. Box Beijing 《热科学学报(英文版)》2003,12(3):198-203
A design procedure for improving the efficiency of a transonic compressor blading was proposed based on a rapid generation method for three-dimensional blade configuration and computational meshes, a three-dimensional Navier-Stokes solver and an optimization approach. The objective of the present paper is to design a transonic compressor blading optimized only by selection of the locations of maximum camber and maximum thickness for the airfoils at different span heights and to study how do these two design parameters affect the blade performance. The blading configuration and the computational meshes can be obtained very rapidly for any given combination of maximum camber and maximum thickness. The computational grid system generated is used for the Navier-Stokes solution to predict adiabatic efficiency, total pressure ratio and flow rate. As a main result of the optimization, adiabatic efficiency was successfully improved. 相似文献
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随着叶轮机械向高膨胀比、高效率的方向发展,叶轮机械级内部越来越多地出现跨音速流动现象。利用数值计算模拟叶轮机械内部的超、跨音速流动,降低激波损失和强度,对提高超、跨音速叶轮机械的性能具有重要意义。 相似文献
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This paper presents a numerical analysis of the atmospheric air transonic flow through de Laval nozzles.By nature,atmospheric air always contains a certain amount of water vapor.The calculations were made using a Laval nozzle with a high expansion rate and a convergent-divergent (CD) "half-nozzle",referred to as a transonic diffuser,with a much slower expansion rate.The calculations were performed using an in-house CFD code.The computational model made it possible to simulate the formation of the liquid phase due to spontaneous condensation of water vapor contained in moist air.The transonic flow calculations also take account of the presence of a normal shock wave in the nozzle supersonic part to analyze the effect of the liquid phase evaporation. 相似文献