轴流压气机非设计点性能计算

胡江峰; 竺晓程; 欧阳华; 羌晓青; 杜朝辉

轴流压气机非设计点性能计算

1.
上海交通大学机械与动力工程学院, 上海 200240
2.
上海交通大学航空航天学院, 上海 200240

基金项目: 国家自然科学基金(51076101/E060203)

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- 文章访问数: 1863
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- 被引次数: 0
出版历程
- 收稿日期: 2011-04-27
- 修回日期: 2011-09-07
- 刊出日期: 2012-03-28

Axial compressor performance calculation at off-design conditions

1.
School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
2.
School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China

摘要

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.
- 流线曲率法 /
- 压气机 /
- 非设计点 /
- 落后角 /
- 损失
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.
- streamline curvature method /
- compressor /
- off-design /
- deviation /
- loss

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参考文献(13)

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