跨音压气机转子近失速工况叶尖非定常流动分析  

Analysis of Near-Tip Unsteady FlowField in a Transonic Compressor Rotor at Near Stall Condition

作　　者：吴艳辉[1] 赵奎[1] 田江涛[1] 楚武利[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《工程热物理学报》2012年第3期401-404,共4页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.51076133);航空科学基金(No.2010ZB53016)

摘　　要：对跨音压气机Rotor35进行单通道全三维定常/非定常数值模拟,并与试验总性能和流场分布对比校核了数值计算精度。以此为基础开展的近失速工况点的非定常计算发现,来自相邻叶片通道未形成泄漏涡的间隙泄漏流体与来流、激波与泄漏涡干涉形成的低能破碎区相互作用形成了叶尖二次涡。叶尖二次涡向下游运动过程中,其所处的位置和产生的阻塞影响了近叶顶载荷的分布,最终使得叶尖部流场出现了循环往复的自维持的非定常波动现象。Three-dimensional single-passage steady and unsteady simulations were carried out to investigate the flowfield in a transonic compressor rotor（Rotor 35）.Via comparing the steady predicted results with the available experimental data,it turned out that,in addition to matching the total performance map well,the predicted results also captured the trend of development of tip leakage vortex（TLV） reasonably well.The further unsteady calculation at near stall condition showed that the tip leakage flow without rolling up into TLV,encountered the incoming flow and then interacted with the low-energy area due to the breakdown of TLV.thus leading to the formation of tip secondary vortex（TSV）.With the rearward movement of TSV,its location and associated blockage resulted in cyclic variation in near-tip blade loading,which in turn lead to the.occurrence of a periodic self-sustained unsteady flow phenomenon in near-tip passage.

关 键 词：轴流压气机 非定常流动 泄漏涡 叶尖二次涡 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]