低雷诺数亚声速扩压平面叶栅试验

凌代军; 王晖; 马昌友

低雷诺数亚声速扩压平面叶栅试验

中国航空工业集团公司中国燃气涡轮研究院,四川江油 621703

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出版历程
- 收稿日期: 2012-01-02
- 刊出日期: 2013-01-28

Subsonic compressor plane cascade experiment at low Reynolds number

China Gas Turbine Establishment, Aviation Industry Corporation of China,Jiangyou Sichuan 621703,China

摘要

摘要: 采用试验方法研究了某亚声速扩压叶型叶片表面和尾迹区气流在低雷诺数条件下的流动特点,获得了叶型损失系数在不同雷诺数情况下的变化规律.试验结果表明:随着低雷诺数降低,叶片表面马赫数分布以及叶栅尾迹区流动均发生剧烈的变化,叶型损失系数也急剧增大;叶型性能变化的转折雷诺数随进口马赫数增大而增大;低雷诺数下叶片吸力面的流动分离是引起叶栅尾迹特性改变和损失系数迅速增大的主要原因.
- 低雷诺数 /
- 平面叶栅 /
- 气动性能 /
- 尾迹区 /
- 损失系数
Abstract: The characteristics of flow in wake area and on blade surface had been obtained by experiment and so was the coefficient changing rule in different Reynolds number conditions.The experimental results show that with the Reynolds number decreasing,great changes happen in wake area and to Mach number distribution on blade surface.At the same time,the loss coefficient of cascade increasing rapidly.At low Reynolds number,the turning Reynolds number of this profile is bigger with the inlet Mach number incresaing.The main reason for loss coefficient increasing and great changes in wake area is the flow separation on suction surface in very low Reynolds number condition.
- low Reynolds number /
- plane cascade /
- aerodynamic performance /
- wake area /
- loss coefficient

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参考文献(16)

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