大小叶片斜流压气机级性能和流场的数值模拟研究  

Exploring Numerically Overall Performance and Flow Field of Mixed Flow Compressor Stage With Splitter Blades

作　　者：黄健[1] 刘振侠[1] 任众[1] 周英庆[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：《西北工业大学学报》2011年第2期283-289,共7页Journal of Northwestern Polytechnical University

摘　　要：文章以某高压比斜流压气机级为研究对象,开展三维定常数值模拟研究,初步获取了压气机级性能和流场结构,并与试验结果进行了对比。结果表明,计算总体性能与试验存在一定的差距,计算的流量-压比曲线比试验值向右和向上移动,流量-效率曲线比试验值向右和略微向上移动。对于斜流叶轮,两个叶片通道出口靠近机匣区域均存在低速流团,通道1中低速流团主要由附面层低能流团在哥氏力作用下堆积而成,通道2中的低速流团主要由叶尖间隙泄漏形成。对于文中计算斜流压气机,通道1中的低速流团对诱发流动失稳起主要作用。Sections 1 and 2 brief our usual method of numerical exploration.Section 3 presents the simulation results of our exploration and their analysis;its core consists of two parts： the simulation results and their analysis.The simulation results are given in Table 1 and Figs.3 through 16 but not including Fig.7.The analysis of simulation results shows preliminarily that：（1） there are discrepancies between the simulation results and experimental data provided by others;（2） compared with the experimental data,the characteristic line of mass flow-pressure ratio moves up and toward the right side;（3） the characteristic line of mass flow-adiabatic efficiency moves up and towards the right side;（4） there are low-velocity stagnation zones near the shroud areas at the outlets of two blade passages of the mixed flow impeller under investigation in this paper;the stagnation zone of Blade Passage 1 is caused by the boundary layer displacement forced by the Coriolis force;the stagnation zone of Blade Passage 2 is caused by the blade tip leakage flow;（5） the stall of the high-pressure ratio mixed flow compressor is mainly caused by the stagnation zone in Blade Passage 1.

关 键 词：压气机 分析 数值模拟 大小叶片 斜流压气机 斜流叶轮 性能 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]