| 摘要: |
| 为更好反映现代轴流风扇内部流动特征,将适合于高马赫数来流的双激波模型引入基元叶栅法,发展了一种多级轴流风扇、压气机非设计点性能计算方法。该方法通过引入雷诺数修正,考虑了雷诺数对风扇/压气机性能的影响,并使最大静压升系数法可在宽广雷诺数变化范围内预测风扇/压气机稳定边界。该方法灵活、可靠,并经过高压压气机、跨声速风扇及大涵道比风扇/增压级等典型的压气机试验结果验证,既可用于多级轴流风扇/压气机非设计点性能计算,又可发展成为高空低雷诺数条件下高性能风扇/压气机设计和研究的重要工具,有着广泛的工程应用前景。 |
| 关键词: 风扇 压气机 基元叶栅法+ 双激波模型+ 边界 雷诺数 |
| DOI： |
| 分类号:V231.3 |
| 基金项目: |
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| Calculation of multistage axial fan/compressor off-design performance |
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ZHAO Yong1, HU Jun2, TU Bao-feng3, WANG Zhi-qiang4
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1.Coll.of Energy and Power Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;2.Coll.of Energy and Power Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210017,China;3.Coll.of Energy and Power Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210018,China;4.Coll.of Energy and Power Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210019,China
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| Abstract: |
| A method to calculate the multistage axial fan/compressor off-design performance was established.It can catch the nature of shock system,and has better accuracy of predicting the loss,owing to a dual-shock loss model suitable for high-speed flow.It is also able to estimate the effects of Reynolds number on the performance of fan/compressor,and the boundary stability of multistage fan/compressor in an extensive range of Reynolds number by means of maximum pressure rise potential.The method is flexible and reliable,validated by test results of three different compressors,such as high-pressure compressor,transonic fan and high bypass ratio fan/booster.Besides predicting the performance of a fan/compressor,it may as a tool of design and researching a fan/compressor in the case of lower Reynolds number.Thus it has an abroad engineering applications foreground. |
| Key words: Fan Compressor Element cascade method+ Dual-shock model+ Boundary Reynolds number |
