共查询到20条相似文献,搜索用时 790 毫秒
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作者应用奇点法对前后缘为任意曲线形状的超音速平板叶栅,导出了一组计算非失速条件下非定常空气动力的公式,编成程序.作为算例用它计算了后掠超音速平板叶栅由于振动引起的非定常空气动力功.这一程序可用来对所设计的超音速叶栅预估是否可能发生颤振提供分析基础,对于指导叶栅设计、避免非失速颤振的发生具有重要的意义. 相似文献
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动静叶栅优化改型及其性能分析 总被引:1,自引:0,他引:1
本文对动静叶栅分别进行优化改型,并对改型前后叶栅的气动性能进行数值分析。动静叶栅的优化改型基于正反问题相结合的流函数方法,性能分析一方面基于单排叶栅定常粘性流动的数值计算,另一方面基于动静叶栅相互干扰非定常粘性流动的数值计算。算例结果表明,经过优化改型后的动静叶栅的气动性能,无论在定常流动条件下还是在非定常流动条件下,相比改型前均有较大幅度的改善。 相似文献
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火电汽轮机低压级组和核电汽轮机/船用核动力汽轮机全级都处于湿蒸汽区,湿蒸汽凝结流动长期以来是影响汽轮机经济性和安全性的难题.针对White叶栅,在吸力面和压力面间设计了一个连接相邻的汽流通道的平行通道,采用双流体模型对原型叶栅和改型叶栅内湿蒸汽凝结特性和气动性能进行研究.以总压损失系数、湿汽损失为评价指标,研究了平行通道开设位置对叶栅性能的影响.研究表明:吸力面开设位置(D点)越靠近叶栅尾缘,改型叶栅除湿性能越好;压力面开设位置(C点)对改型叶栅除湿性能影响不大;C点和D点越靠近叶栅尾缘,总压损失系数越大. 相似文献
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一、序言 文献[1]介绍了后掠超音速叶栅由于振动引起的非定常空气动力的计算方法,用它可预估超音速叶栅非失速颤振。文献[1]的理论也可用来计算变动来流干扰引起的作用于叶片上的非定常空气动力以及因之而产生的噪音。本文介绍其方法的概要和一些算例。 这方面,梶,岡崎和西山,小林对于直叶栅、難波对于旋转叶栅、菊地对于超音速叶栅进行了研究。菊地着重考察了前置静叶在周向倾斜时的三元影响,本文着重考 相似文献
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采用理论和实验的方法研究了一定汽水参数下的超音速汽液两相流升压装置的极限升压能力以及主要结构参数对其的影响规律。计算与实验的结果表明:超音速汽液两相流升压装置的极限升压能力计算值可达进汽压力的14倍左右,实验值可到进汽压力的2.6倍左右;混合腔和水喷嘴的几何尺寸是影响极限升压能力的最主要的结构参数;极限升压能力随混合腔收缩比增大而增大,随水喷嘴出口与混合腔喉部截面积比增大而减小,随蒸汽喷嘴喉部与出口截面积之比变化不大。计算和实验得到的结构参数对极限升压能力的影响规律是基本一致的。 相似文献
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Chan S. K. Fang M. T. C. Cowley M. D. 《IEEE transactions on plasma science. IEEE Nuclear and Plasma Sciences Society》1978,6(4):394-405
The boundary layer integral method at its second level of approximation has been used to study the DC arc in a supersonic nozzle flow. It is shown that with the inclusion of the arc momentum balance, the critical point of the flow is, generally, not the sonic point of the external flow. The speed, at which a disturbance propagates relative to the external flow, is in general supersonic and is dependent on the arc conditions. The arc model is capable of predicting the axial electric field, the arc size and the axial pressure distribution as a function of current. For affinely related nozzles, the solution is determined by a parameter N, which is related to zt, the stagnation condition and the nominal current density at the throat (I/At). Numerical results are given for a particular nozzle shape although the method of analysis is general. Practical implications as regards nozzle design for a gas blast circuit breaker are briefly discussed. 相似文献
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F. Quintero J. Pou J.L. Fernndez A.F. Doval F. Lusquios M. Boutinguiza R. Soto M. Prez-Amor 《Optics and Lasers in Engineering》2006,44(11):1158-1171
The aerodynamic features of the gas flow during laser fusion cutting are an essential factor influencing the cut performance. For this reason it has been a subject of some studies to explain the interactions of the gas jet with the workpiece and to design different gas injection systems with the aim of preventing the drawbacks of the conventional cutting heads.An off-axis cutting head with a de Laval nozzle to inject a supersonic gas jet has been previously demonstrated to be an effective design to achieve a complete removal of the molten material from the cutting front and to avoid the formation of the recast layer. In the present work, the fundamentals and procedures to adjust the main factors determining the efficiency of this gas injection system are described. Specifically, the gas flow inside the cut kerf is analysed by means of flow visualization using the Schlieren technique. 相似文献
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进气道是超声速飞行器的关键部件,设计核心是无黏超声速流场的确定,而波系结构又直接决定了流场的性能。考虑到实际应用价值,基于给定激波的超声速流场反设计至关重要。传统单道入射波的流场结构简单,压缩效率不高,且传统特征线法(method of characteristics,MOC)无法获得高阶的气动参数。为了拓展设计思路,首先利用弯曲激波特征线法展示了内收缩超声速流场不同的单元过程,随后基于此法提出了一种已知入射和反射激波的两级压缩内收缩流场的概念及反设计方法。基于此法设计的基准流场与数值模拟结果吻合良好,双入射激波可以提高压缩效率并缩短长度,能够实现波系结构和出口参数的分布可控,在非均匀来流条件下也能得到相应型面。在给定激波的条件下,求解分析了一系列具有中心体的轴对称流场,讨论入射和反射激波激波角分布对流场气动参数和几何参数的影响。弯曲激波特征线法的精确性和有效性使其成为平面/轴对称超声速流场反设计的良好候选。 相似文献
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为研究多喷管超声速引射器在有二次流情况下的性能,采用模拟器产生给定总温和总压的模拟二次流,在多喷管超声速引射器实验台上进行了一系列实验。重点考察了多喷管引射器的性能以及一次流总压和喷管安装构型对其性能的影响。实验结果表明:多喷管超声速引射器可保证二次流在设计工况下正常工作;二次流的加入大大减小了一次流的总压损失;较低的一次流总压具有更好的压力匹配性能,但引射增压能力也有所降低;合理的喷管安装构型可同时提高引射增压能力和压力匹配能力。提出了将二次流作为“助推器”,以帮助多喷管引射器在较低工况下实现启动的方案,在不增加系统复杂度的前提下提高了引射器的压力匹配能力。 相似文献
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A mathematical unsteady pseudoshock model describing the continuous transition from supersonic to subsonic flow is constructed for a barotropic gas flow in a long flat channel or a nozzle. The model is based on a two-layer scheme of flow with mass transfer including a potential supersonic core and a turbulent boundary layer. 相似文献
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Experimental investigations have indicated that electrode vapor can have a significant negative effect in thermal interruption speed for the gas-blast circuit breakers. This electrode vapor contamination can be minimized by the use of asymmetric dual-flow nozzle configuration. A computer program was developed to design the nozzle and electrode geometries of the asymmetric dual-flow interrupter and to calculate both the subsonic and supersonic cold flow fields. The Variational Principle of the finite element method, together with a Newton-Raphson iterative scheme, was used to solve the continuity equation for compressible flow. The supersonic flow field in the conical nozzle was calculated by the one-dimensional flow relationship. Two asymmetric dual-flow nozzle models were constructed to investigate the effects of orifice opening and nozzle divergent angle. The cold flow experiments were conducted in the Rensselaer Polytechnic Institute (RPI) Transonic and Supersonic Wind Tunnel Laboratory. Various upstream-to-downstream nozzle pressure ratios were used to obtain the subsonic and supersonic experimental flow-field data. The experimental flow measurements were correlated with the calculated values to validate the computer program. 相似文献
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基于吸气式高超声速飞行器机体/推进一体化的气动布局设计方式,文章提出了一种内外流一体化流场的耦合求解方法,其中燃烧室内流场采用考虑有限速率化学反应动力学模型的一维非稳态方法求解,进气道和尾喷管外流场采用二维CFD软件计算,进气道与燃烧室在耦合界面处通过一维平均方法实现静温、静压和Mach数等参数传递.并分别以日本国家航空与航天实验室(NAL)的氢燃料燃烧室模型作为内流场验证算例,以某典型高超声速飞行器一体化模型作为内外耦合流场验证算例.研究结果表明:有限速率化学反应准一维方法能较为准确地模拟燃烧室内燃烧流场,提出的内外流场耦合方法能够有效地计算出内外流耦合效应,计算后体压力分布与理论值较接近.该方法可为超燃冲压发动机的性能快速分析和吸气式高超声速飞行器机体/推进一体化的初步分析设计提供重要参考. 相似文献