弯曲叶片积叠线对压气机叶栅气动性能的影响  

Effects of Curved Blade Stacking Line on the Aerodynamic Performance of Compressor Cascade

作　　者：王会社[1] 袁新[1] 岳国强[2] 钟兢军[2] 王仲奇[2] 

机构地区：[1]清华大学热能工程系,北京100084 [2]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：《航空动力学报》2002年第3期327-331,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目 (5 0 0 760 0 9;5 0 0 760 19) ;973 (G19990 2 2 3 0 6;G19990 2 2 3 0 7) ;全国优秀博士学位论文作者专项基金资助项目 (19993 2 )

摘　　要：本文采用拟压缩性方法对不同积叠线弯曲叶片压气机叶栅内三维粘性流场进行了数值模拟。结果表明 ,弯曲叶片性能不仅与叶片两端部的弯曲角度有关 。The numerical simulation has been carried out to investigate the three dimensional viscosity flow in the compressor cascades with curved blades of different types of stacking lines.The method of the pseudo compressibility was used and the incompressible Navier Stokes equations were solved.The results show that the performance of curved blade is influenced not only by the end angle, but also by the shape and length of the stacking line.

关 键 词：弯曲叶片 积叠线 压气机叶栅 气动性能 影响 拟压缩方法 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]