摘要
为了研究叶片不同正弯曲角度对压气机叶栅气动性能的影响 ,在平面叶栅低速风洞上 ,对具有可控扩散叶型 (CDA)的直叶片和 15° ,2 0° ,2 5°正弯曲叶片压气机叶栅进行了实验。获得了不同弯曲角度扩压叶栅出口流场的能量损失系数、涡量以及叶片表面静压系数等的分布。结果表明 ,叶片正弯曲 2 0°时叶栅总损失降低最多 ,达16 15 %。正弯曲叶片吸力面形成“C”型压力分布 。
To investigate the influence of the blade positive curved angle on the performance of compressor cascade, experiments were conducted in a low speed wind tunnel with planar cascade. Rectangle compressor stator cascades consisting of four types of blades with controlled diffusion airfoils were tested. These include: Straight blades, positive curved angle 15°, 20°, and 25° blades. The distribution of energy loss coefficient and vorticity at all cascade qxits and static pressure coefficient on blade surface are acguired. The results show that the loss of curved blade cascade is reduced. When the degree of curved angle is 20°, the loss of the cascade is least, and it is 16.15% less than the straight blade cascade. On suction surface of positive curved blade, the C type static pressure distribution is created, and this distribution is enhanced with the increase of the blade curved angle.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2002年第4期321-324,共4页
Journal of Propulsion Technology
基金
国家自然科学基金 (5 0 0 76 0 0 9)
教育部全国优秀博士学位论文作者专项基金 (199932 )
"九七三"资助项目(G19990 2 2 30 7)
