近零冲角下环型压气机叶栅的弯曲叶片表面静压的研究  

A Study of the Surface Static Pressure of Curved Blades in Annular Compressor Cascades at Near-zero Incidence

作　　者：王东[1] 苏杰先[2] 钟兢军[2] 王仲奇[2] 

机构地区：[1]上海交通大学机械与动力学院,上海200030 [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：《热能动力工程》2003年第4期369-371,374,共4页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金资助项目(59636180)

摘　　要：在环型扩压叶栅实验风洞上对近零冲角进口流场畸变下的常规直叶栅、正倾斜叶栅、正弯曲叶栅、S型叶栅进行了叶片表面静压测量,分析了不同的弯曲叶片对表面静压分布的影响。结果表明正弯曲叶片、正倾斜叶片和S型叶片可以提高根部静压,减小了低能流体在轮毂区的堆积,流场结构大为改善,轮毂区的气流分离和堵塞减轻,提高了扩压能力,降低轮毂区的端壁损失。On an annular diffusion cascade experimental wind tunnel detailed measurements of traditional straight, positive leaned, positively curved and S type blades of annular axial flow compressor cascades were carried out under an inlet flow field distortion at near zero incidence. The impact of different curved blades on the distribution of surface static pressure is analyzed. The results of the analysis indicate that the use of the positive leaned, positive curved and S type blades can lead to an increase in blade root static pressure and a reduction in the accumulation of low energy fluid at the hub region. This will result in a considerable improvement of the flow field configuration and a lessening of gas flow separation and blockage at the hub region, thus enhancing diffusion capability and decreasing the end wall loss at the hub region.

关 键 词：叶片弯曲 环型扩压叶栅 叶片表面静压 压气机 航空发动机 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]