叶片前缘不同后掠角对离心压气机气动性能的影响  

Back-swept Leading Edge Effects on Aerodynamic Performance of Small Scale Transonic Centrifugal Compressor

作　　者：郭龙凯 刘艳明[1] 崔庆[1] 王丽华[2] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]南京信息工程大学信息与控制工程学院,江苏南京210044

出　　处：《热能动力工程》2016年第4期45-51,143-144,共7页Journal of Engineering for Thermal Energy and Power

基　　金：清华大学汽车安全与节能重点实验室开放基金资助项目(KF14011);国家自然科学基金青年基金资助项目(51405241)

摘　　要：采用全三维气动设计技术,设计了4种具有掠角叶片和带翼型叶片扩压器的涡轮增压跨音速离心压气机,并采用数值模拟手段研究了叶片前缘不同后掠角对压气机内部工质流动的影响。研究结果表明:主叶片前缘不同后掠角会使压气机堵塞流量(堵塞工况下的工质流量)增加,提高压气机流通能力,同时,可以有效改善通道内低能流团的分布;但由于主叶片轴向弦长缩短,会造成喘振裕度的减少,以及主叶片前缘脱体激波角增大和槽道激波的增强;对截面二次流分析结果表明:叶片前缘的后掠角对二次流的影响主要表现在叶轮进口附近,对出口影响不大。对比不同前缘后掠角压气机内部流动情况发现,掠角越小,叶片叶顶负荷越小,叶片表面压差也越小,流动越稳定;掠角越大,虽然叶轮通道上游产生的激波越强烈,但是可以明显改善通道下游气流流动情况。Four transonic compressors with swept blades and wing-type diffusers are designed by a fully three-dimension CFD technique. And numerical simulation is also carried out to investigate the influence of back-swept leading edge on the flow field of compressor. The results show that the blades with back-sweptness can increase the choke mass flow and enhance ability of circulation. At the same time,back-sweptness can improve the distribution of the low energy mass flow. But because of the blade's chord reduced which will reduce the surge margin,it also can increase the leading shock wave angle and strengthen the shock wave in the channel. Back-sweptness has a greater effect on the secondary flow at S3 section near the impeller inlet than the outlet. From the cases of different back-swept angles,it is found that,as the back swept angle becomes smaller,the pressure difference between suction side and pressure side becomes much smaller,and simultaneously the flow field is more stable. When the back swept angle becomes greater,the separation zone becomes weaker and weaker,although the shock wave is stronger. The smaller back swept angle can suppress the formation of separation vortex near the diffuser outlet.

关 键 词：跨音速 涡轮增压离心压气机 二次流 前缘后掠角 激波 

分 类 号：TK402[动力工程及工程热物理—动力机械及工程]