进口附面层对大转角弯曲扩压叶栅气动性能的影响

陈绍文; 陈浮; 王仲奇

进口附面层对大转角弯曲扩压叶栅气动性能的影响

哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

基金项目: 国家自然科学基金(50646021);高等学校博士学科点专项科研基金(20060213007)

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出版历程
- 收稿日期: 2007-07-05
- 修回日期: 2007-10-26
- 刊出日期: 2008-07-28

Effects of inlet boundary layar on aerodynamic performance of bowed compressor cascades with large camber angle

Energy Science and Engineering School, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 在低速条件下,对不同进口附面层厚度的大折转角环形弯曲扩压叶栅进行了实验和数值研究,分析了在不同厚度的进口附面层条件下叶片弯曲对扩压叶栅气动性能的影响.结果表明,相比实验进口附面层条件,当进口附面层较薄时,在多数冲角情况下采用正弯叶片对叶栅气动性能的改善程度都有所增大,而较大正冲角时,在较大折转角叶栅中采用较大弯角的正弯曲叶片仍然引起损失激增.
- 进口附面层 /
- 扩压叶栅 /
- 弯曲叶片 /
- 叶型折转角
Abstract: The annular bowed compressor cascads with large camber angle under different inlet boundary layers thicknesses were investigated experimentally and numerically under low-speed condition.The effects of bowed blade on aerodynamic performance of compressor cascade were analyzed under different inlet boundary layer thicknesses.The results show that,when the inlet boundary layer is getting thinner,the aerodynamic performance of cascades improves under most flow conditions.However,the total loss will rise sharply if bowed blade with bigger incidences is adopted in the cascade with larger camber angle when the bowed angle is bigger.
- inlet boundary layer /
- compressor cascade /
- bowed blade /
- camber angle

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参考文献(7)

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