共查询到20条相似文献,搜索用时 125 毫秒
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提出了一种基于自然样条思想的弯叶片生成方法,推导了其积迭线的解析表达式.通过控制"弯度"参数可获得不同角度的弯叶片.将该弯叶片生成方法运用于某型冷却风扇,通过数值模拟研究了叶片各种弯曲形式对风扇气动性能的影响.结果表明:叶片前弯能有效抑制叶顶旋涡,降低叶顶区域的能量损失,扩大叶轮稳定工况范围;圆弧型弯叶片的风压略大于自然样条型弯叶片,但后者对降低叶顶区域能量损失更具明显优势. 相似文献
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应用拓扑学原理分析了叶顶相对间隙为0.036的涡轮直叶栅与正、反弯叶栅的壁面流谱,发现正弯叶片栅与直叶片、反弯叶片栅吸力面上半叶展的拓扑结构明显不同,探讨了差别形成的机理及其对相对漏气量与总流动损失的影响。 相似文献
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对比研究了直叶片叶栅与弯叶片叶栅吸力面角区和下端壁流场显示的不同表现,发现弯叶片对角区分离流结构影响较大,它对减小端区马蹄涡尺度和减弱横向二次流作用明显。将不同叶栅中三维流向涡(通道涡和集中脱落涡)沿流向截面内的位置与强度作为研究对象,细致地分析了在采用弯叶片前后涡位置和强度的变化,分析表明两种涡的位置受弯叶片影响较大;通道涡沿流向的强度变化受弯叶片影响较为明显,而集中脱落涡强度受弯叶片影响却很小。来流马赫数、叶型折转角和稠度在一定范围内对弯叶片作用有规律性影响:当马赫数为0.7时,最佳弯角弯叶片降低损失7%.而马赫数为0.2时,最佳弯角弯叶片降低损失仅4%。 相似文献
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跨音轴流压气机动叶的三维弯掠设计研究 总被引:3,自引:0,他引:3
对一单级跨音轴流压气机中的动叶分别进行了前掠和正弯设计的参数研究,并根据研究得到的弯、掠动叶气动性能变化规律对动叶进行了前掠和正弯联合的三维设计,同时对动叶中部截面的叶型进行了二维设计以弥补弯掠动叶中部性能的降低.最终设计的跨音级性能显著提高,级最大效率提高3%,失速裕度提高40%,同时压比有所增加.数值计算结果表明,前掠和正弯叶片都可以使叶顶激波位置移向下游,降低激波强度,减轻叶顶激波与边界层和泄漏涡的作用.弯掠动叶控制激波强度和端壁流动的能力更加突出. 相似文献
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Efficient method to handle the geometric constraints in the optimization of turbomachinery blade profile is required. Without constraints on the blade thickness, optimal designs typically yield thinner blade to reduce the friction loss, however, at the risk of degraded strength and stiffness. This issue is seldom discussed and existing literature always treat the blade thickness constraint in an indirect manner. In this work, two different geometric constraints on the blade thickness are proposed and applied in the adjoint optimization: one is on the maximum blade thickness and the other is on the blade area. Methods to compute sensitivities of both constraints are proposed and they are integrated into an optimization system based on a finite volume code and a solver for the discrete adjoint equation. Adjoint optimization is conducted to minimize the entropy production in a transonic compressor stage. Results for the adjoint optimization without geometry constraint and two comparative cases are detailed. It is indicated that three cases yield similar performance improvement; however, if geometry constraints are properly handled, the optimal designs have almost the same maximum thickness as the original design, compared to a thinner blade profile with 14% reduction of maximum thickness in the case without geometry constraint. The cases considering geometry constraints also consume slightly reduced Central Processing Unit(CPU) cost. Result of this work verifies the effectiveness of the proposed method to treat geometric constraints in adjoint optimization. 相似文献
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Sameh Shaaban 《国际能源研究杂志》2017,41(12):1767-1780
Despite the fact that wave energy is available at no cost, it is always desired to harvest the maximum possible amount of this energy. The axial flow air turbines are commonly used with oscillating water column devices as a power take‐off system. The present work introduces a blade profile optimization technique that improves the air turbine performance while considering the complex 3D flow phenomena. This technique produces non‐standard blade profiles from the coordinates of the standard ones. It implements a multi‐objective optimization algorithm in order to define the optimum blade profile. The proposed optimization technique was successfully applied to a biplane Wells turbine in the present work. It produced an optimum blade profile that improves the turbine torque by up to 9.3%, reduces the turbine damping coefficient by 10%, and increases the turbine operating range by 5%. The optimized profile increases the annual average turbine power by up to 3.6% under typical sea conditions. Moreover, new blade profiles were produced from the wind turbine airfoil data and investigated for use with the biplane Wells turbine. The present work showed that two of these profiles could be used with low wave energy seas. Copyright © 2017 John Wiley & Sons, Ltd. 相似文献
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具有良好灵活性的高精度叶型参数化建模方法对于压气机叶型设计和优化具有重要影响。本文研究了一种基于非有理B样条曲线理论(NURBS)曲线组和遗传算法的轴流压气机叶片参数化建模方法。该方法基于中弧线厚度叠加法,采用两条三次七点NURBS曲线分别构造中弧线形状和厚度分布,前尾缘采用双二次NURBS曲线,通过多段曲线光滑拼接实现叶片造型。以压气机型线方差值最小作为目标函数,利用遗传算法实现了叶型的参数化建模。通过数值模拟实验证明,本文提出的参数化造型方法适用于高亚音速压气机叶型的参数化建模。 相似文献
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A parametric method for the axial compressor 2D blade profiles is proposed in which the blade geometries are defined with the parameters commonly used for blade definition, which ensures that the geometric significance is clear and an unreasonable blade profile is not generated. Several illustrations are presented to show the fitting precision of the method. A novel response surface model is proposed which regards the objective distribution function in the vicinity of a sample as normal school, and then generates the response surface function in the whole design space by a linear combination of distribution functions of all the samples. Based on this model, a numerical aerodynamic optimization platform for the axial compressor 2D blade profiles is developed, by which aerodynamic optimization of two compressor blade profiles are presented. 相似文献
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常规风力机叶片的优化设计都是从二维翼型开始的,且翼型总是以升阻比最大为优化目标。然而,二维翼型的升阻比最大和三维叶片的高风能利用率与低气动载荷有本质的不同,采用以往的叶片优化方法常常会在提高风能利用率的同时,使叶片所受的气动载荷也提高。针对这一问题,提出基于多岛遗传算法和动量叶素理论,在给定风况条件下,以加权风能利用率最高与气动载荷最小为目标函数,以叶片各个截面的翼型型线及扭角作为设计变量,对三维叶片开展多目标优化方法设计研究。并对某实际NREL Phase VI叶片进行优化设计,结果表明:在给定风况下相比原叶片,优化叶片在风能利用率提升了3.06%的基础上,叶根弯矩降低了11.68%。在变转速与变风况下,优化叶片的气动效率整体提升,叶根弯矩明显降低。 相似文献
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Numerical optimization of axial turbine with self‐pitch‐controlled blades used for wave energy conversion
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Wells turbines are among the most practical wave energy converters despite their low aerodynamic efficiency and power produced. It is proposed to improve the performance of Wells turbines by optimizing the blade pitch angle. Optimization is implemented using a fully automated optimization algorithm. Two different airfoil geometries are numerically investigated: the standard NACA 0021 and an airfoil with an optimized profile. Numerical results show that each airfoil has its own optimum blade pitch angle. The present computational fluid dynamics optimization results show that the optimum blade pitch angle for NACA 0021 is +0.3° while that of the airfoil with an optimized profile equals +0.6°.The performance of the investigated airfoils is substantially improved by setting the blades at the optimum blade pitch angle. Both the turbine efficiency and tangential force coefficient are improved, especially at low flow rate and during turbine startup. Up to 4.3% average increase in turbine efficiency is achieved by optimizing the blade pitch angle. A slight improvement of the tangential force coefficient and decrease of the axial force coefficient are also obtained. A tangible increase of the stall‐free operating range is also achieved by optimizing the blade pitch angle. Copyright © 2013 John Wiley & Sons, Ltd. 相似文献
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变叶片数和长短叶片对某跨音速向心汽轮机气动性能的影响 总被引:1,自引:0,他引:1
利用三维数值模拟的方法对一跨音速向心汽轮机进行了气动设计优化分析,通过改变叶片数和采用长短叶片结构等方法分析其对叶轮内流场的影响,分析了TC-4P叶型的气动特点。结果表明:TC-4P叶型虽然只是普通的渐缩型流道的叶栅,但利用其斜切部的膨胀能力,对超音速工况一样具有良好的性能;叶轮采用长短叶片的方法可以有效地降低余速损失,并改善流动状况。 相似文献
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A parametric method for the axial compressor 2D blade profiles is proposed in which the blade geometries are defined with
the parameters commonly used for blade definition, which ensures that the geometric significance is clear and an unreasonable
blade profile is not generated. Several illustrations are presented to show the fitting precision of the method. A novel response
surface model is proposed which regards the objective distribution function in the vicinity of a sample as normal school,
and then generates the response surface function in the whole design space by a linear combination of distribution functions
of all the samples. Based on this model, a numerical aerodynamic optimization platform for the axial compressor 2D blade profiles
is developed, by which aerodynamic optimization of two compressor blade profiles are presented.
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Translated from Acta Aeronautica et Astronautica Sinica, 2007, 28(4): 813–820 [译自: 航空学报] 相似文献