大弯度可控扩散叶型叶栅槽道中气体流动的试验研究  

INVESTIGATION OF FLOWS IN A CONTROLLED DIFFUSION AIRFOLL CASCADE PASSAGE

作　　者：程荣辉 仲永兴 严汝群[1] 

机构地区：[1]西北工业大学

出　　处：《航空动力学报》1993年第3期221-224,共4页Journal of Aerospace Power

摘　　要：本文对一种大弯度可控扩散叶型叶栅槽道和栅后流场进行了测量 ,并对端壁和叶片表面进行了流动显示。通过研究 ,对叶栅槽道特别是端部气体流动 ,旋涡结构以及二次流影响有深入的了解。本文的工作对于改进压气机端部流动条件 ,发展第二代可控扩散叶型有重要的实际意义。This paper presents the flow measurement in the blade passage and downstream of a high turning controlled diffusion airfoil(CDA)cascade in details and the investigation of flow visualization on the endwall and blade surface.As a result,a thorough comprehension is obtained in respect of the flow in the blade passage especially in the endwall area,the vortex structure and of the effect of endwall boundary layer and secondary flow on the performance of the cascade.It is of great practical value in improving the flow conditions in the endwall area of a compressor and developing the second generation of the controlled diffusion airfoil.

关 键 词：弯度 可控扩散叶型 叶栅 发动机 

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]