| 分流叶片轮缘进口角对离心压气机性能影响数值仿真 |
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| 引用本文： | 王海朋,王聪,常国强,徐夏.分流叶片轮缘进口角对离心压气机性能影响数值仿真[J].航空发动机,2018,44(3):21-25. |
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| 作者姓名： | 王海朋 王聪 常国强 徐夏 |
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| 作者单位： | 南京模拟技术研究所 |
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| 摘 要： | 为了研究分流叶片轮缘进口角的变化对离心压气机级性能的影响,以某小型模型级离心压气机为研究对象,利用数值仿真软件对流场进行了全3维模拟,重点分析其内部流场结构的变化。数值仿真结果表明:分流叶片轮缘进口角对离心压气机性能影响明显,其角度的增加使离心压气机的压比和效率提高,但会缩小离心压气机的稳定工作范围。
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| 关 键 词： | 离心压气机 分流叶片 数值模拟 |
Numerical Simulation of Effect of Splitter Blade Tip Inlet Angle on Performance of Centrifugal Compressor |
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| Authors: | WANG Hai-peng WANG Cong CHANG Guo-qiang XU Xia |
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| Institution: | Nanjing Research Institute on Simulation Technique,Nanjing 210016,China |
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| Abstract: | Abstract: To study the effect of splitter blade tip inlet angle changes on performance of centrifugal compressor, full 3D simulation of
the flow field of a small model centrifugal compressor was made using numerical simulation software, the changes of its inner flow field
structure were mainly analyzed. The results show that the splitter blade tip inlet angle has a great influence on performance of centrifugal
compressor,the pressure ratio and efficiency of the centrifugal compressor improve with the angle increase, however,the stable operating
range of the centrifugal compressor reduces. |
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| Keywords: | centrifugal compressor splitter blade numerical simulation |
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