采用弯叶片的不同折转角压气机叶栅流场气动性能  

Aerodynamic performance study of curved compressor cascades with different camber angles

作　　者：陈绍文[1] 陈浮[1] 王可立[1] 谷君[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2007年第2期170-175,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(50236020)

摘　　要：实验研究了叶片弯曲对不同叶型折转角环形扩压叶栅气动性能的影响,分析了叶栅出口总压损失和二次流速度矢量分布,并给出了壁面静压分布及壁面墨迹流动显示结果。研究结果表明,叶型折转角越大损失分布的对称性越差,根部损失增加明显;弯曲角度和叶型折转角的增大将使得正弯叶栅吸力面反“C”型静压分布加剧,60°叶型折转角叶栅中径处负荷随叶片弯曲角度变化的敏感性强,大弯角时气流易分离,导致总损失激增;综合来说,对比直叶栅,正弯15°叶栅在各种叶型折转角正弯叶栅中减小损失效果最好。The effects of dihedral on the aerodynamic performance in annular compressor cascades with different camber angles has been experimentally investigated. The distribution of exit total pressure loss and secondary flow vectors of the compressor cascades were analyzed. The static pressure was measured by tapping on the cascade surfaces and ink-trace flow visualizations was also conducted. The results show that with the increase of camber angle, the symmetry of the loss distribution is less symmetrical and the loss at the hub increases more greatly. With the increase of camber angle and curved angle, opposite C-shape static pressure distribution on suction surface of curved cascades become more acutely. The load near the midspan of compressor cascades with 60°camber angle is so sensitive to the curved angle changing and this easily results in the flow separation under large curved angle and the increase of total loss. To sum up, compared with straight cascade, the efficiency of the curved cascade with 15°curved angle decreasing loss is optimal in different camber angles.

关 键 词：压气机 叶栅 叶片 气动力试验 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]