A compressor automated optimization system was investigated
which composed of software ISIGHT
NUMECA and a sophisticated blade-design program.For testing its validity
a single-stage transonic compressor was optimized by changing circumferential stacking line of blade.The results show efficiency and pressure ratio is improved in whole characteristic curve;the investigation indicated the negative bow of rotor tip can improve flow structure and validated the compressor automated optimization system.
Numerical study on three-dimensional optimization of low-speed axial compressor rotor blade
Optimization design of centrifugal/oblique flow compressor two-dimensional blade profiles in three-dimensional environment
Optimum airfoil design on an heavy amphibious aircraft
Design research of supersonic fan blade profile
考虑多源不确定性的复合材料风扇叶片高周疲劳失效概率评估
Related Author
ZHANG Chen-kai
HU Jun
WANG Zhi-qiang
YIN Chao
YAN Wei
TAO Sheng
ZHOU Zheng-gui
YAN Xin
Related Institution
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
Collaborative Innovation Center for Advanced Aero-Engine
Unit 95874, the Chinese People's Liberation Army
Aerodynamics Department,Research Institute Company Limited, China Aviation Industry Generaal Aircraft Corporation Limited Aviation Industry Corporation of China
College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics