摘要
实验在低速环形风洞上研究了冲角变化对不同弯曲角度、不同叶型折转角扩压叶栅气动性能的影响.结果表明,随着叶型折转角的增大,正弯叶栅变冲角性能的最佳弯角范围逐渐缩小,大折转角正弯叶栅的气动性能受冲角变化的影响要大于小折转角叶栅正弯叶栅;在正冲角下,60°叶型折转角正弯叶栅性能对弯角变化十分敏感,此时不宜采用超过15°弯角的正弯叶栅.
The experimental investigation of the effects of changing incidences on the aerodynamic performance of compressor cascades with different curved angles and camber angles in a low-speed annular wind tunnel were carried out . Experimental results show that with the increase of camber angle, the choice range of curve height correspond to the best performance in different incidences become narrower. The effects of incidence angles on the aerodynamic performance of positive curved cascades with large camber angle are more evident contrast to with small camber angle. The performance of positive curved cascades with 60°camber angle is so sensitive to the curved angle changing at higher incidence angles, so that a positive curved cascades with larger curved angles than 15°is inadvisable.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第3期406-411,共6页
Journal of Aerospace Power
基金
国家自然科学基金项目(50236020)资助
关键词
航空
航天推进系统
叶栅实验
弯曲叶片
冲角
叶型折转角
aerospace propulsion system
cascade experiment
curved blade
incidence
camber angle
