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基于遗传算法的2 维叶型优化设计
引用本文:刘龙龙,周正贵,陶胜.基于遗传算法的2 维叶型优化设计[J].航空发动机,2014,40(5):50-56.
作者姓名:刘龙龙  周正贵  陶胜
作者单位:南京航空航天大学能源与动力学院,南京,210016
摘    要:为得到具有宽广低损失工作范围的静子叶片,采用基于遗传算法的优化平台对3个不同载荷水平的静子叶栅叶型的型面、安装角及弦长进行优化设计。通过比较3个叶栅优化前后的正常特性线,认为尾缘"负载荷区域"对改善叶栅性能是有益的,且其对叶栅性能的改善效果与叶片载荷有关。结果表明:优化后叶栅性能在设计点和非设计点都有明显改善;叶片表面等熵马赫数分布类似控制扩散叶型,最大载荷点位置前移,叶型前段弯度增加,尾缘出现"负载荷区域"。

关 键 词:静子叶片  压气机  数值优化  遗传算法  负载荷  航空发动机

Optimization Design on 2D Blade Profiles Based on Genetic Algorithm
Authors:LIU Long-long  ZHOU Zheng-gui  TAO Sheng
Institution:College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Abstract:In order to get stator blades with low loss in a wide range of attack angle, three stator blades profiles of different load levels were optimized by the genetic algorithm. According to contrasting the normal characteristic behind and after three cascades optimized, the negative load region on the trailing edge was significant for improving the cascade performance, which affects the optimized results and blade loadings of cascade performance. The results show that the optimized cascade performance has obvious improvements for design conditions and off design conditions. The distributions of isentropic Mach number on the blade surfaces is similar with the controlled diffusion profiles, the position of maximum loads moves forward, camber increased in front of blades, and the "negative load region" appears on the trailing edge.
Keywords:stator blade  compressor  numerical optimization  genetic algorithm  negative load  aeroengine
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