扩压叶栅角区马蹄涡的实验研究

EXPERIMENTAL STUDY OF HORSESHOE VORTEX IN THE CORNER REGION OF A LINEAR COMPRESSOR CASCADE

本文给出了用三维激光多普勒测速技术对扩压叶栅叶片前缘马蹄涡的测量结果。实验结果表明：在０°和１０°两种攻角条件下均存在清晰的前缘马蹄涡；二次流的影响使得在靠近端壁壁面的区域实际入口气流角和叶片中径处不同，在不同的攻角条件下这种影响也不同；前缘马蹄涡的存在使得接近前缘的气流方向改变，气流角增大。

The paper presents the results of an experimental investigation at low speed in the corner region of a linear compressor cascade. The measurements were carried out in the large-size wind tunnel at speed of 9 m/s. Mean velocities were measured by using a three-dimensional laser Doppler velocimeter. The measurements have revealed the horseshoe vortex structure and have permitted to determine the global structure of the flow around the leading edge of the blade. The actual incident angle of flow near the endwall were different with experimental condition due to the secondary flow which the velocity profile were skewed. At various incident angle of flow condition below this influence also different.