一种高负荷叶型优化设计方法

赵清伟; 潘若痴

doi:10.13224/j.cnki.jasp.2016.12.026

一种高负荷叶型优化设计方法

doi: 10.13224/j.cnki.jasp.2016.12.026

中国航空发动机集团有限公司沈阳发动机研究所, 沈阳 110015

详细信息

作者简介:
赵清伟(1985-),男,黑龙江海伦人,工程师,硕士,主要从事风扇/压气机气动设计及研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2016-07-02
- 刊出日期: 2016-12-28

A method of optimal design of highly-loaded airfoil

Shenyang Engine Research Institute, Aeronautical Engine(Group) Corporation of China, Shenyang 110015, China

摘要

摘要: 采用3段3次贝塞尔曲线拟合叶型中弧线弯角分布，两段3次贝塞尔曲线拟合厚度分布，进行流线面造型，并结合优化算法进行寻优.S1流场评价工具为MISES软件，寻优算法为遗传算法（GA）.将传统遗传算法进行改进，引入并行模块，较大程度地提高了计算效率.实现了高负荷叶型的自动优化，探讨了高负荷叶型的设计准则，并将准则应用于超声叶型设计.结果表明：相比于原始叶型，优化后的叶型Ⅰ在总压损失系数略降低和出口气流角不变的条件下，可用攻角范围拓宽约2°，叶型Ⅱ的总压损失系数明显降低，可用攻角范围拓宽约0.6°，落后角降低约3.9°.
- 高负荷叶型 /
- 遗传算法(GA) /
- 优化 /
- 贝塞尔曲线 /
- MISES软件
Abstract: 3-section of cubic Bezier spline was used to fit the tangent of camber line and 2-section of cubic Bezier spline was used to fit the thickness distribution. The airfoil was built on streamline-surface. S1 flow field was evaluated by MISES software and optimization algorithm was performed by genetic algorithm(GA). By introducing a parallel mode to the traditional GA, computational efficiency was improved considerably. Automatic design and optimization of highly-loaded airfoil was achieved and the design criteria of highly-loaded airfoil for design of supersonic airfoil were investigated. Results show that compared with the original airfoil, incident angle range of airfoil I is broadened about 2 degree under the premise that loss coefficient of total pressure reduces a little and the airflow angle of outlet is unchanged; if loss coefficient of total pressure of airfoil II obviously reduces, incident angle range is broadened about 0.6 degree and deviation angle reduces about 3.9 degree.
- highly-loaded airfoil /
- genetic algorithm(GA) /
- optimization /
- Bezier spline /
- MISES software

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