| 超音轴向分速风扇/压气机叶栅流动特征分析 |
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| 引用本文： | 马继华,陶德平.超音轴向分速风扇/压气机叶栅流动特征分析[J].北京航空航天大学学报,1990(2). |
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| 作者姓名： | 马继华 陶德平 |
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| 作者单位： | 北京航空航天大学动力系
(马继华)，北京航空航天大学动力系(陶德平) |
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| 摘 要： | 本文介绍了三种带冲波的超音轴向分速叶型设计,及其叶栅流场计算,分析了这些叶栅流场特征。在计算的反压条件下,全部波系均控制在槽道内,叶栅槽道内存在不同大小的轴向分速超音区,这种叶型叶栅可承受的增压比高,总压恢复系数较低,这类叶栅的性能和流动特征尚缺少实验数据和理论分析。
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| 关 键 词： | 超音轴向分速 叶型设计 叶栅流场计算 等马赫线分布 |
ANALYTICAL STUDY ON FAN/COMPRESSOR CASCADE FLOW CHARACTERISTICS WITH SUPERSONIC AXIAL VELOCITY COMPONENT |
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| Ma Jihua Tao Deping.ANALYTICAL STUDY ON FAN/COMPRESSOR CASCADE FLOW CHARACTERISTICS WITH SUPERSONIC AXIAL VELOCITY COMPONENT[J].Journal of Beijing University of Aeronautics and Astronautics,1990(2). |
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| Authors: | Ma Jihua Tao Deping |
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| Institution: | Power Department |
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| Abstract: | Three types of supersonic axial velocity blades with shock design are introduced.It also presents a calculation of the cascade flow field and an analysis of its features.under the calculated back pressure conditions,all the shocks are controlled within the passage and different supersonic axial velocity areas exist.It is proved that this kind blade can bear higher pressure with a high pressure ratio and a relatively low total pressure recovery efficiency,however,the performance and the flow characteristics of this type of cascade need to be further identified through experiment and calculation. |
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| Keywords: | supersonic axial velocity component airfoil design cascade flowfield calculation mach number contours |
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