多级轴流压气机全三维流动特性的数值研究  

Understanding Better "Artificial Total Pressure Loss" in Multi-Stage Axial-Flow Compressor

作　　者：高丽敏[1] 刘海湖[2] 刘波[1] 陈云永[1] 

机构地区：[1]西北工业大学动力与能源学院翼型叶栅国防重点实验室,陕西西安710072 [2]西安交通大学能源与动力学院,陕西西安710049

出　　处：《西北工业大学学报》2008年第1期1-5,共5页Journal of Northwestern Polytechnical University

基　　金：教育部博士点新教师基金(20070699034);西北工业大学高层次人才科研启动费;西北工业大学“翱翔之星”计划资助

摘　　要：文中分别以一低转速的2级半轴流式压气机与一高转速的3级半轴流压气机为研究对象,采用混合界面模型对其全流量工况下的流动进行了数值研究。计算采用Jam eson的4步Runge-K utta时间推进方法结合中心差分格式求解N-S方程,级间采用混合界面方法实现上下游叶排流动信息的传递。研究结果表明:采用混合界面方法产生的"人工"掺混会导致总压损失及界面处流动参数的间断,而且转速对界面处的"人工"的总压损失有明显影响;但是对于低压、低转速的多级轴流压气机,采用混合界面方法能够较为准确快速的预测其多流量工况下的气动性能。Aim. To our knowledge, owing to computational complexity, previous research that used mixing plane approach was, in our opinion, poor in information about ＂artificial total pressure loss＂. We now explore the ＂artificial total pressure loss＂ of multistage axial-flow compressor with five blade rows or more. In the full paper, we explain our exploration in some detail; in this abstract, we just add some pertinent remarks to listing the two topics of explanation. The first topic is： numerical methods. In the first topic, we mention that four step Runge-Kutta time-marching method by Jameson with the central difference scheme is employed to resolve the N-S equations. Also in the first topic, we point out that the flow information between two adjacent rows is exchanged between each other by the mixing-plane approach. The second topic is. numerical results and their analysis. In the second topic, we give two numerical examples： a 2.5 stage axial-flow compressor and a 3.5 stage one. Figs. 1 through 4 give the numerical results for 2. 5stage compressor and Figs. 5 through 7 give those for the 3.5 stage compressor. The analysis of these results shows preliminarily that： （1） ＂the artificial total pressure loss＂ and the discontinuity of the flowfield occur on the interface between two adjacent rows due to the ＂artificial mixing＂ of the mixing plane approach; （2） the rotational speed of the axial-flow compressor has a distinct influence on the ＂artificial total pressure loss＂; （3） but for an axial-flow compressor with both rotational speed and pressure ratio low, its aerodynamic performance could be predicted accurately and quickly using the mixing plane method.

关 键 词：轴流压气机 气动性能 混合界面 数值模拟 

分 类 号：O345.2[理学—固体力学]