肋片影响下的压气机静子叶栅流动特性研究  

Flow Characteristics of Compressor Stator Cascades Affected by Ribs

作　　者：赵晨旭 傅鑫[1] ZHAO Chenxu;FU Xin(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2023年第3期54-57,共4页Machine Building & Automation

摘　　要：研究了肋片结构对带静子容腔的压气机静子叶栅的影响,采用数值模拟方法分析进气攻角及马赫数变化带来的流动性能变化。结果表明:增加肋片后,低能流体的发展变得复杂,有肋片时出口总压损失下降了4.53%,叶根处叶片载荷增大,叶根角区流场恶化得到缓解。从总体来看总压损失随攻角增大均有所增加,正攻角时叶根处流场性能严重恶化。随马赫数增加,100%轴向弦长处的总压损失逐渐增大,10%叶高处叶片载荷逐渐降低。The influence of the rib structure on the compressor stator cascade with stator cavity is studied,and the changes of the flow performance caused by the change of inlet attack-angle and inlet Mach number are analyzed by numerical simulation method.The results show that the development of low-energy fluid becomes more complicated with the addition of ribs,the total pressure loss at the outlet decreases by 4.53%in the presence of ribs,the blade load increases at the blade root,and the deterioration of the flow field at the blade root corner is alleviated.In general,the total pressure loss increases with the increase of the attack angle,and the flow field performance at the blade root deteriorates seriously when the attack angle is positive.With the increase of Mach number,the total pressure loss at 100%of the axial chord length gradually increases,and the blade load at 10%of the blade height gradually decreases.

关 键 词：压气机 上游容腔优化 肋结构 流场分布 总压损失 叶片载荷 

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]