Aerodynamic optimization design of a single stage compressor

被引：0

作者：

Xue, Liang ^{[1
]}

Han, Wan-Jin ^{[1
]}

Huang, Jia-Hua ^{[2
]}

Meng, Ding ^{[3
]}

机构：

[1] School of Energy Science and Engineering, Harbin Inst. of Technology, Harbin 150001, China

[2] The Second Artillery Representative Office in the 31st Research Inst., Beijing 100074, China

[3] The Second Artillery Representative Office in 699 Machinery Factory, Beijing 100039, China

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2009年 / 30卷 / 04期

关键词：

Compressors - Aerodynamics - Genetic algorithms - NASA;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

Aerodynamic optimization design for a single row of blade may not ensure its stage performance, so the optimization design for the matching of rotor with stator is performed in a single stage of transonic compressor. Multipoint aerodynamic optimization design for NASA Stage35 is performed, including the aerodynamic operating point and the maximum efficiency point. In the design, rotor sweeping, leaning and stator curving is applied to be as the design variables. An optimized compressor stage is obtained with the rotor forward swept and the stator curved towards its pressure side. The stage performances at all working conditions are improved.

引用

页码：419 / 424

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