向心涡轮跨声速导向叶片叶型设计及验证  

Design and validation of transonic nozzle guide vane profile of radial-inflow turbine

作　　者：欧阳玉清 李维 曾飞 潘尚能 李恩华 刘存良[1] OUYANG Yuqing;LI Wei;ZENG Fei;PAN Shangneng;LI Enhua;LIU Cunliang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2023年第5期1217-1225,共9页Journal of Aerospace Power

摘　　要：以某先进辅助动力装置用膨胀比5.0级向心涡轮跨声速导叶为研究对象,从消除几何喉部前局部超声区及削弱尾缘激波强度两方面着手,对导向叶片进行了优化改进及叶栅试验验证,结果表明:采用大正攻角、小安装角的设计思路,减小喉部前吸力面叶型曲率,降低进口段的通道面积,提高了叶型前段负荷,消除了喉部前的过膨胀区,喉部前气流加速更为均匀;在吸力面喉部后构建局部内凹结构,可将原方案中吸力面尾缘处一道较强的激波变为两道较弱的激波,峰值马赫数降低,尾缘逆压梯度减小,尾缘激波强度得以削弱。试验结果显示:在出口马赫数0.9~1.1范围内,优化后叶型能量损失系数均有所降低,在出口马赫数为1.1时,能量损失系数可降低近20%。Taking the transonic nozzle guide vane of a radial-inflow turbine with expansion ratio of 5.0 for an advanced auxiliary power unit as the research object,the vane profile was optimized and cascade tests were conducted by eliminating the local ultrasonic region in front of the throat and weakening the shock wave intensity at the trailing edge.The research showed that by adopting the design idea of large positive incidence angle and small installation angle,and reducing the curvature of suction side before the throat,reducing the flow area of inlet duct,the load in front of the blade profile was improved,the over expansion area before the throat was eliminated,and the airflow acceleration was more uniform.A local concave structure was constructed behind the throat of the suction surface,which can transform one strong shock wave at the trailing edge of the suction surface into two relatively weak shock waves.The peak Mach number decreased,and the adverse pressure gradient at the trailing edge decreased,weakening the strength of the trailing edge shock wave.The test results indicated that the energy loss coefficient of optimized profile dropped as the cascade exit Mach numbers varied from 0.9 to 1.1,and the energy loss coefficient dropped nearly 20%when the exit Mach number was 1.1.

关 键 词：向心涡轮 跨声速叶栅 导向器叶片 叶型设计 激波损失 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]