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孔隙射流位置对直扩压叶栅壁面静压及流谱影响
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作者 陈浮 冯冬民 +1 位作者 傅丽鹏 王仲奇 《工程热物理学报》 EI CAS CSCD 北大核心 2008年第11期1844-1846,共3页
对带有孔隙射流的某大折转角直扩压叶栅性能进行了实验研究,分析了不同位置孔隙射流对壁面静压及极限流线的影响.结果表明,孔隙射流能够改善角区流动,同时降低叶片中部损失;最佳开孔位置位于25%相对叶高处,总压损失系数相对无孔隙射流... 对带有孔隙射流的某大折转角直扩压叶栅性能进行了实验研究,分析了不同位置孔隙射流对壁面静压及极限流线的影响.结果表明,孔隙射流能够改善角区流动,同时降低叶片中部损失;最佳开孔位置位于25%相对叶高处,总压损失系数相对无孔隙射流叶栅降低4.9%;孔隙位置对端壁静压的影响不大. 展开更多
关键词 孔隙射流 压气机叶栅实验 大折转角 表面静
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低负荷和高负荷压气机叶栅气动性能的实验和数值模拟 被引量:2
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作者 原泽 郑群 +2 位作者 岳国强 董静涛 姜玉廷 《航空动力学报》 EI CAS CSCD 北大核心 2021年第4期724-733,共10页
为了明确采用高负荷设计及一般设计(低负荷)方法的压气机气动性能和流动转捩的差异,进行了不同攻角下的叶栅吸力面流谱绘制和参数测量实验。并基于实验边界条件,采用γ-θ转捩模型开展数值研究。结果表明:与低负荷叶栅相比,随着攻角的增... 为了明确采用高负荷设计及一般设计(低负荷)方法的压气机气动性能和流动转捩的差异,进行了不同攻角下的叶栅吸力面流谱绘制和参数测量实验。并基于实验边界条件,采用γ-θ转捩模型开展数值研究。结果表明:与低负荷叶栅相比,随着攻角的增大,高负荷叶栅主流附面层由附着流变为分离流,尾迹的宽度和损失强度增加,并与角区分离融合为一个"带状"损失区。而低负荷叶栅的角区分离仍为紧贴壁面的开式分离,主流附面层仍然附着在壁面上。结果表明:高负荷设计增强了叶栅内逆压力梯度,这使得流动更容易分离,表现为表面形状因子呈现大范围的"峰谷"型分布,转捩模式也由局部旁路转捩变为全叶高范围的分离泡转捩。 展开更多
关键词 低负荷和高负荷 压气机叶栅实验 动性能 转捩 攻角
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Experimental and Numerical Investigation on Compressor Cascade Flows with Tip Clearance at a Low Reynolds Number Condition 被引量:3
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作者 Hiromasa Kato Hideo Taniguchi +3 位作者 Kazunari Matsuda Ken-ichi Funazaki Dai Kato Guillaume Pallot 《Journal of Thermal Science》 SCIE EI CAS CSCD 2011年第6期481-485,共5页
High flow rate aeroengines typically employ axial flow compressors, where aerodynamic loss is predominantly due to secondary flow features such as tip leakage and comer vortices. In very high altitude missions, turbo-... High flow rate aeroengines typically employ axial flow compressors, where aerodynamic loss is predominantly due to secondary flow features such as tip leakage and comer vortices. In very high altitude missions, turbo- machinery operates at low density ambient atmosphere, and the recent trend toward more compact engine core inevitably leads to the reduction of blade size, which in turn increases the relative height of the blade tip clearance. Low Reynolds number fiowfield as a result of these two factors amplifies the relative importance of secondary flow effects. This paper focuses on the behavior of tip leakage flow, investigating by use of both experimental and numerical approaches. In order to understand the complex secondary flow behavior, cascade tests are usually conducted using intrusive probes to determine the loss. However relatively few experimental studies are pub- lished on tip leakage flows which take into account the interaction between a rotating blade row and its casing wall. Hence a new linear cascade facility has been designed with a moving belt casing in order to reproduce more realistic flowfield as encountered by a rotating compressor row. Numerical simulations were also performed to aid in the understanding of the complex flow features. The experimental results indicate a significant difference in the flowfield when the moving belt casing is present. The numerical simulations reveal that the leakage vortex is pulled by the shearing motion of the endwall toward the pressure side of the adjacent blade. The results highlight the importance of casing wall relative motion in analyzing leakage flow effects. 展开更多
关键词 COMPRESSOR tip leakage flow
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