跨音压气机转子叶尖流场中诱导涡的讨论和分析  

Discussion and Analysis of Induced Vortex in Transonic Compressor Rotor Tip Flow

作　　者：贾一哲[1] 晁晓亮 杨雄[1] 高翔[1] 

机构地区：[1]中国飞行试验研究院,西安710000

出　　处：《科学技术与工程》2017年第17期351-356,共6页Science Technology and Engineering

摘　　要：Van Zante等首次提出了诱导涡的概念,在研究诱导涡与压气机叶尖流场的关系之前需要回答"诱导涡是否存在"这一问题。为此以跨音转子NASA Rotor 35为研究对象,采用四种不同的网格配置在80%设计转速下进行单通道数值模拟。数值计算均捕捉到了流场的主要特征,与实验结果符合较好;但没有出现所谓的诱导涡,因此对叶尖区流场的关注焦点仍然可以集中在叶顶间隙泄漏流本身。尽管如此,近机匣壁网格不断加密还是会对泄漏流的轨迹产生影响;因此Van Zante等提出的用来评估壁面剪切层强弱的参数VD依旧具有参考价值,只是针对其物理意义的解释需要重新阐述。Van Zante et al. proposed the concept of induced vortex for the first time. It is necessary to answer the question of whether or not induced vortex exists before studying the relationship between the induced vortex and the tip clearance flow. The NASA Rotor 35 is used as the research object,and the single-channel numerical simulation is performed at 80% design speed with four different grid configurations. The main characteristics of the flow field are captured by the numerical simulation,which is in good agreement with the experimental results,but no socalled induced vortex exists. Therefore,the research focus of the tip field can still concentrate on the tip clearance flow itself. However,if the grid cells in the tip gap are clustered at the shroud,it will affect the trajectory of the tip clearance flow. Therefore,the parameter VD proposed by Van Zante et al. to evaluate the strength of the wall bounded shear layer is still valuable,but the explanation of its physical meaning needs to be re-elaborated.

关 键 词：NASA ROTOR 35 80%转速 诱导涡 叶顶间隙泄漏流 

分 类 号：V231.21[航空宇航科学与技术—航空宇航推进理论与工程]