| 全三维、多叶排内外涵风扇压气机叶型优化研究 |
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| 引用本文： | 陈云永,刘波,马聪慧,高丽敏,石建成,温泉.全三维、多叶排内外涵风扇压气机叶型优化研究[J].航空动力学报,2008,23(3):516-521. |
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| 作者姓名： | 陈云永 刘波 马聪慧 高丽敏 石建成 温泉 |
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| 作者单位： | 1. 西北工业大学,翼型、叶栅国防重点实验室,西安,710072
2. 中国航空动力机械研究所,株洲,412002 |
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| 基金项目： | 航空科学基金(04C53022)，航空支撑基金(04B53007) |
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| 摘 要： | 以某风扇/压气机为研究对象,采用全三维叶型优化方法对研究对象在整机条件下进行优化设计.对优化前后风扇/压气机进行全三维数值模拟并对计算结果进行对比分析研究,结果表明:优化后在不改变风扇级总压比的情况下设计点附近效率提高1.05%;在近设计点叶型改进后明显改善了风扇和外涵静子主流道的流场结构,根、尖两个截面流场显示采用新叶型后对内、外涵静子通道内流动均有不同程度的改善.
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| 关 键 词： | 航空、航天推进系统 风扇/压气机 特性 叶型优化 流场分析 |
| 文章编号： | 1000-8055(2008)03-0516-06 |
| 收稿时间： | 2007/3/19 0:00:00 |
| 修稿时间： | 2007年3月19日 |
Three-dimension blade optimization of multi-blade fan/compressor |
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| CHEN Yun-yong,LIU Bo,MA Cong-hui,GAO Li-min,SHI Jian-cheng and WEN Quan.Three-dimension blade optimization of multi-blade fan/compressor[J].Journal of Aerospace Power,2008,23(3):516-521. |
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| Authors: | CHEN Yun-yong LIU Bo MA Cong-hui GAO Li-min SHI Jian-cheng and WEN Quan |
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| Affiliation: | National Defence Aerodynamics Laboratory of Airfoil and Cascade, Northwestern Polytechnical University, Xi'an 710072, China;National Defence Aerodynamics Laboratory of Airfoil and Cascade, Northwestern Polytechnical University, Xi'an 710072, China;National Defence Aerodynamics Laboratory of Airfoil and Cascade, Northwestern Polytechnical University, Xi'an 710072, China;National Defence Aerodynamics Laboratory of Airfoil and Cascade, Northwestern Polytechnical University, Xi'an 710072, China;China Aviation Power Plant Research Institute, Zhuzhou 412002, China;China Aviation Power Plant Research Institute, Zhuzhou 412002, China |
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| Abstract: | With the help of software Fine/Design 3D and a computational fluid dynamics(CFD) method,the optimization design of a three-dimensional blade was carried out for fan/compressor.Then three-dimensional numerical simulation software named Fine/Turbo was used to calculate typical working conditions of both the new fan/compressor and the initial one at design rotating speed.The flow field performance under design speed condition was obtained.Numerical results show that efficiency is increased by 1.05% at design point after optimization of fan blade,without changing the stage total pressure ratio.The optimization obviously improves,especially in the fan stream,the flow structure and parameters of the fan/compressor's main flow. |
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| Keywords: | aerospace propulsion system fan/compressor characteristics blade optimization flow field analysis |
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