| 轴流压气机超音叶片叶型几何设计方法的研究 |
| |
| 引用本文： | 肖敏,刘波,仲永兴.轴流压气机超音叶片叶型几何设计方法的研究[J].航空动力学报,2000,15(3):237-240. |
| |
| 作者姓名： | 肖敏 刘波 仲永兴 |
| |
| 作者单位： | 1. 中国燃气涡轮研究院,四川,江油,621703
2. 西北工业大学704教研室,陕西,西安,710072 |
| |
| 摘 要： | 本文研究了3种超音压气机叶型中弧线几何设计方法,讨论了控制叶型前缘进口区曲率的参数及其变化关系;进行了叶栅设计和流场数值计算分析,结果表明:设计叶型表面马赫数分布理想,激波结构合理,但以指数中弧线法最佳.
|
| 关 键 词： | 轴流压气机 叶片 叶型 设计 |
| 收稿时间： | 7/7/1999 12:00:00 AM |
| 修稿时间： | 1999-07-07 |
A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor |
| |
| Xiao Min,Liu Bo and Zhong Yongxing.A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor[J].Journal of Aerospace Power,2000,15(3):237-240. |
| |
| Authors: | Xiao Min Liu Bo and Zhong Yongxing |
| |
| Institution: | Aero.Gas Turbine Establishment,Jiangyou 621703,China;7th Dept.Northwest Polytechnic University,Xi'an 710072,China;Aero.Gas Turbine Establishment,Jiangyou 621703,China |
| |
| Abstract: | Three geometric methods for designing supersonic airfoil meanline are studied.The parameters which control curvature in the leading region of airfoil and their variations are considered.The flow fields of the cascade designed with these methods are analyzed.It is shown that the Mach number distribution of designed blade surface is ideal,shock wave structure is reasonable.But the exponential method is superior. |
| |
| Keywords: | axial flow compressor blade blade profile design |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
