轴流压气机非设计点性能计算
Axial compressor performance calculation at off-design conditions
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摘要: 采用流线曲率法数学模型,结合跨声速轴流压气机的内部流场特征,拓展了一种非设计点特性计算方法.该方法基于近年来的国内外研究进展,考虑了非设计点工况下影响落后角及损失的诸多因素.对轴流跨声速压气机NASA(National Aeronautics and Space Administration)TP1669进行了数值计算,得到了展向参数分布和全工况下性能曲线,通过与实验值的对比和分析证明该方法和模型是可行的,可为压气机设计和优化提供参考.Abstract: The axial compressor performance prediction method was developed,based on streamline curvature method,according to the flow mechanics of transonic axial compressor.This method considered the series impacts of deviation and loss to a certain extent according to the national and international openning research progresses.The internal flow field of NASA(National Aeronautics and Space Administration) TP1659 was calculated,thus obtained the span-wise aerodynamic parameters and characteristic curves at design and off-design points.With the comparison between simulation and experimental value,this method and models are validated to be applicable,and can be used for compressor design and optimization.
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Key words:
- streamline curvature method /
- compressor /
- off-design /
- deviation /
- loss
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