离心压气机导风轮叶顶端壁引气扩稳研究  

Inducer tip endwall bleeding effects on centrifugal compressor stability enhancement

作　　者：康剑雄[1,2] 黄国平[1] 朱俊强[2] 温殿忠[3] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国科学院工程热物理研究所轻型动力重点实验室,北京100190 [3]中国航空工业集团公司中国航空动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2014年第11期2561-2569,共9页Journal of Aerospace Power

基　　金：基础科研项目(B1320110070)

摘　　要：对一台在导风轮叶顶设置有自循环机匣处理的离心压气机,借鉴其试验结果制定了3种引气位置A,B和C,并结合不同的引气量进行了端壁引气扩稳的数值研究.计算结果表明:引气位置和引气范围对扩稳效果有重要影响,引气位置C覆盖了整个叶尖回流区,引气面积最大,扩稳效果最好.随引气量的变化,出现了两种不同的扩稳机理:小引气量可以吸除叶尖泄漏流,缓解通道阻塞,延缓端壁失速;过大的引气量则挤占有效流通面积,将通流区域压向轮毂侧,增加了叶轮的做功能力.兼顾压气机的效率考虑,小引气量具有优势,引气位置C用5%引气量可以获得19.6%的裕度提升.Numerical simulation was carried out to explore the benefit of inducer tip endwall bleeding effects on centrifugal compressor stability enhancement.Based on the experimental results of the centrifugal compressor with a self-recirculating casing treatment on top of inducer,three tip bleeding configurations（A,B and C）with different bleed rates were simulated.The result shows that bleed position and bleed range have grate influence on stability enhancement effect.Configurations C is the best location because it has the largest bleeding area covers the whole tip backflow zone.Additionally,with the variation of suction flow rate,there are two different mechanisms of stability extension.When the flow rate is low,bleeding can suppress the tip leakage flow and remove low momentum fluid,so the channel blocking will be reduced to delay endwall stall.Otherwise,larger rate of suction flow will occupy the channel and the main flow will be pushed towards hub side to improve the rim power of the rotor.Considering the compression efficiency,lower bleeding rate has advantages.For configuration C,5%is the optimum bleed rate with the margin increase by 19.6%.

关 键 词：导风轮 端壁引气 机匣处理 总压比 效率 失速裕度 

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]