| 冲压空气涡轮性能的局部改进升力线算法 |
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| 引用本文： | 张剑锋,刘思永.冲压空气涡轮性能的局部改进升力线算法[J].北京航空航天大学学报,1997,23(4):482-486. |
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| 作者姓名： | 张剑锋 刘思永 |
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| 作者单位： | 北京航空航天大学动力系 |
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| 摘 要： | 将现代螺旋桨的改进升力线算法应用于空气涡轮性能计算，结合冲压空气涡轮结构特性对叶片模化作了局部改进，对一个冲压空气涡轮模型作了计算，与实验结果和改进升力线法的对比表明，局部改进后的叶片环量和诱导速度分布合理，计算精度和宽度有明显改善，与实验符合较好。
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| 关 键 词： | 冲压空气涡轮 升力线 尾涡 航空发动机 |
PARTLY IMPROVED LIFT LINE ALGORITHM OF RAM AIR TURBINE PERFORMANCE |
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| Zhang Jianfeng\ \ Liu Siyong.PARTLY IMPROVED LIFT LINE ALGORITHM OF RAM AIR TURBINE PERFORMANCE[J].Journal of Beijing University of Aeronautics and Astronautics,1997,23(4):482-486. |
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| Authors: | Zhang Jianfeng\ \ Liu Siyong |
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| Abstract: | The modern propeller improved lift line algorithm has been applied to Ram Air Turbine performance calculating.The blade modeling is partly improved with Ram Air Turbine construction character.Comparison with experiments and improved lift line,results carried out for a Ram Air Turbine model shows good agreement with experiments and the distributions of blade circulation and induced velocities are reasonable,precision and width are improved obviously. |
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| Keywords: | ram air turbine lift line trailing vortex |
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